Started by upstream project "ESP_bPreBuilt" build number 77 originally caused by: Started by user galbramc Running as galbramc [EnvInject] - Loading node environment variables. Building remotely on macys_VM in workspace /Users/jenkins/workspace/ESP_bPreBuilt [WS-CLEANUP] Deleting project workspace... [WS-CLEANUP] Deferred wipeout is used... [WS-CLEANUP] Done Checking out a fresh workspace because there's no workspace at /Users/jenkins/workspace/ESP_bPreBuilt Cleaning local Directory . Checking out svn+ssh://acdl.mit.edu/home/svnroot/OpenCSM/trunk/Jenkins at revision '2024-07-27T23:59:51.894 -0400' --quiet Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ At revision 2518 Checking out a fresh workspace because /Users/jenkins/workspace/ESP_bPreBuilt/JenkinsESP doesn't exist Cleaning local Directory JenkinsESP Checking out svn+ssh://acdl.mit.edu/home/svnroot/JenkinsESP at revision '2024-07-27T23:59:51.894 -0400' --quiet Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ At revision 882 Checking out a fresh workspace because /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023 doesn't exist Cleaning local Directory CAPS/training/2023 Checking out svn+ssh://acdl.mit.edu/home/svnroot/CAPS/training/2023 at revision '2024-07-27T23:59:51.894 -0400' --quiet Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ At revision 4251 No changes for svn+ssh://acdl.mit.edu/home/svnroot/OpenCSM/trunk/Jenkins since the previous build Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ Using sole credentials 3614a4cf-01de-4393-97de-73734b7dd5a2 in realm ‘svn+ssh://acdl.mit.edu’ [GitCheckoutListener] SCM 'hudson.scm.SubversionSCM' is not of type GitSCM Run condition [Execution node ] enabling prebuild for step [Execute shell] Run condition [Execution node ] enabling prebuild for step [Execute shell] Run condition [Execution node ] enabling prebuild for step [Execute Windows batch command] [Execution node] check if [macys_VM] is in [[macys, macys_VM, master, reynolds, reynolds-centOS7, reynolds-centOS8, reynolds-rhel7, reynolds-ubuntu16, reynolds-ubuntu18, reynolds-ubuntu20]] Run condition [Execution node ] enabling perform for step [Execute shell] [ESP_bPreBuilt] $ /bin/bash -xe /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T/jenkins14803164292654395812.sh + bash -ex /Users/jenkins/workspace/ESP_bPreBuilt/JenkinsESP/ESP_PreBuilt.sh + source /Users/jenkins/workspace/ESP_bPreBuilt/JenkinsESP/ESP_Env.sh ++ export OCCTREF=7.8 ++ OCCTREF=7.8 ++ AFLR_VERSION=11.5.15 ++ SU2_VERSION=8.0.1 ++ TETGEN_VERSION=1.6.0 ++ VSP_VERSION=3.38.0 ++ export PYTHON_VERSION=3.11.9 ++ PYTHON_VERSION=3.11.9 ++ export MPLBACKEND=agg ++ MPLBACKEND=agg ++ export EFCOMP=gfortran ++ EFCOMP=gfortran ++ [[ macys_VM == \r\e\y\n\o\l\d\s ]] ++ [[ '' == *\.\i\f\o\r\t ]] ++ '[' -f /opt/intel/oneapi/setvars.sh ']' ++ source /opt/intel/oneapi/setvars.sh ++ '[' -f /Users/jenkins/.bashrc ']' ++ export CAPS_OUTLEVEL=0 ++ CAPS_OUTLEVEL=0 ++ export ESP_UDC_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/personalUdc ++ ESP_UDC_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/personalUdc ++ [[ '' == \D\A\R\W\I\N\6\4\.\g\c\c ]] ++ export ESP_BLOC=/Users/jenkins/workspace/ESP_bPreBuilt/ESP/ ++ ESP_BLOC=/Users/jenkins/workspace/ESP_bPreBuilt/ESP/ ++ export ESP_ROOT=/Users/jenkins/workspace/ESP_bPreBuilt/ESP/ ++ ESP_ROOT=/Users/jenkins/workspace/ESP_bPreBuilt/ESP/ ++ export JULIA_DEPOT_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP//julia ++ JULIA_DEPOT_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP//julia ++ export AWAVE=awavemod.f ++ AWAVE=awavemod.f ++ export RLM_CONNECT_TIMEOUT=350 ++ RLM_CONNECT_TIMEOUT=350 ++ [[ 7.8 != '' ]] ++ [[ '' != '' ]] ++ [[ macys_VM == *\r\e\y\n\o\l\d\s* ]] ++ [[ macys_VM == *\m\a\c\y\s* ]] ++ export EMPnumProc=2 ++ EMPnumProc=2 ++ export OMP_NUM_THREADS=2 ++ OMP_NUM_THREADS=2 ++ source /Users/jenkins/.bash_profile +++ [[ -r /usr/local/etc/profile.d/bash_completion.sh ]] +++ . /usr/local/etc/profile.d/bash_completion.sh ++++ '[' -z '3.2.57(1)-release' -o -z '' -o -n '' ']' ++++ return +++ export PATH=/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin +++ PATH=/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin +++ export PATH=/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin +++ PATH=/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin ++ [[ macys_VM == *\m\a\c\y\s* ]] ++ export PATH=/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ PATH=/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ [[ macys_VM == \m\a\c\y\s ]] ++ export CASARCH=. ++ CASARCH=. ++ '[' '!' -z '' ']' +++ ls -d '/Users/jenkins/util/ESP/OpenCASCADE-.?' ls: /Users/jenkins/util/ESP/OpenCASCADE-.?: No such file or directory ++ export CASROOT= ++ CASROOT= ++ export UDUNITS2_XML_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP/udunits/udunits2.xml ++ UDUNITS2_XML_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP/udunits/udunits2.xml ++ export ESP_EXTERN_LIBS=/Users/jenkins/util/ESP/ExternLibs ++ ESP_EXTERN_LIBS=/Users/jenkins/util/ESP/ExternLibs ++ export DYLD_LIBRARY_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP//lib:/lib:/opt/intel/oneapi/tbb/2021.3.0/env/../lib:/opt/intel/oneapi/mkl/2021.3.0/lib:/opt/intel/oneapi/compiler/2021.3.0/mac/compiler/lib/intel64_mac:/opt/intel/oneapi/compiler/2021.3.0/mac/compiler/lib ++ DYLD_LIBRARY_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP//lib:/lib:/opt/intel/oneapi/tbb/2021.3.0/env/../lib:/opt/intel/oneapi/mkl/2021.3.0/lib:/opt/intel/oneapi/compiler/2021.3.0/mac/compiler/lib/intel64_mac:/opt/intel/oneapi/compiler/2021.3.0/mac/compiler/lib ++ export AFLR=/Users/jenkins/util/AFLR/aflr_lib_11.5.15 ++ AFLR=/Users/jenkins/util/AFLR/aflr_lib_11.5.15 ++ [[ macys_VM == *\m\a\c\y\s* ]] ++ export AFLR_ARCH=MacOSX-x86-64 ++ AFLR_ARCH=MacOSX-x86-64 ++ export ASTROS_ROOT=/Users/jenkins/util/astros/Astros/Darwin-64bit ++ ASTROS_ROOT=/Users/jenkins/util/astros/Astros/Darwin-64bit ++ export PATH=/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ PATH=/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ export CART3D=/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16 ++ CART3D=/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16 ++ export CART3D_ARCH=OSX64_ICC ++ CART3D_ARCH=OSX64_ICC ++ export PATH=/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ PATH=/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ export PATH=/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ PATH=/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ export PATH=/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ PATH=/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ export VSP3_ROOT=/Users/jenkins/util/OpenVSP/OpenVSP-3.38.0-MacOS ++ VSP3_ROOT=/Users/jenkins/util/OpenVSP/OpenVSP-3.38.0-MacOS ++ export PATH=/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ PATH=/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/ ++ [[ macys_VM == \m\a\c\y\s ]] ++ [[ macys_VM == \v\i\g\g\e\n ]] ++ [[ macys_VM == \v\i\g\g\e\n ]] ++ export SU2_HOME=/Users/jenkins/util/SU2/SU2-v8.0.1 ++ SU2_HOME=/Users/jenkins/util/SU2/SU2-v8.0.1 ++ export SU2_RUN=/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ SU2_RUN=/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ export PATH=/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PATH=/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ export PYTHONPATH=:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PYTHONPATH=:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ export TETGEN=/Users/jenkins/util/tetgen/tetgen1.6.0 ++ TETGEN=/Users/jenkins/util/tetgen/tetgen1.6.0 ++ export PATH=/Users/jenkins/util/tsfoil:/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PATH=/Users/jenkins/util/tsfoil:/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ '[' -d /Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16 ']' ++ export PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin:/Users/jenkins/util/tsfoil:/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin:/Users/jenkins/util/tsfoil:/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ export PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP//test:/Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin:/Users/jenkins/util/tsfoil:/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP//test:/Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin:/Users/jenkins/util/tsfoil:/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ export PYTHONPATH=/Users/jenkins/workspace/ESP_bPreBuilt/EGADS/trunk/pyEGADS::/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PYTHONPATH=/Users/jenkins/workspace/ESP_bPreBuilt/EGADS/trunk/pyEGADS::/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ export PYTHONPATH=/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/pyOCSM:/Users/jenkins/workspace/ESP_bPreBuilt/EGADS/trunk/pyEGADS::/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PYTHONPATH=/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/pyOCSM:/Users/jenkins/workspace/ESP_bPreBuilt/EGADS/trunk/pyEGADS::/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ export PYTHONPATH=/Users/jenkins/workspace/ESP_bPreBuilt/CAPS/pyCAPS:/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/pyOCSM:/Users/jenkins/workspace/ESP_bPreBuilt/EGADS/trunk/pyEGADS::/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PYTHONPATH=/Users/jenkins/workspace/ESP_bPreBuilt/CAPS/pyCAPS:/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/pyOCSM:/Users/jenkins/workspace/ESP_bPreBuilt/EGADS/trunk/pyEGADS::/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ [[ macys_VM == \m\a\c\y\s* ]] ++ mkdir -p /Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin ++ rm -f /Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin/python ++ rm -f /Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin/python-config ++ rm -f /Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin/virtualenv ++ rm -f '/Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin/analyze-*' ++ rm -f '/Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin/intercept-*' ++ [[ macys_VM == \m\a\c\y\s ]] ++ [[ macys_VM == \v\i\g\g\e\n ]] ++ ln -s /usr/local/bin/python3 /Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin/python ++ ln -s /usr/local/bin/python3-config /Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin/python-config ++ ln -s /usr/local/bin/virtualenv /Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin/virtualenv +++ python-config --includes ++ export 'PYTHONINC=. -I/usr/local/opt/python@3.11/Frameworks/Python.framework/Versions/3.11/include/python3.11 -I/usr/local/opt/python@3.11/Frameworks/Python.framework/Versions/3.11/include/python3.11' ++ PYTHONINC='. -I/usr/local/opt/python@3.11/Frameworks/Python.framework/Versions/3.11/include/python3.11 -I/usr/local/opt/python@3.11/Frameworks/Python.framework/Versions/3.11/include/python3.11' +++ python-config --help ++ [[ Usage: /Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin/python-config [--prefix|--exec-prefix|--includes|--libs|--cflags|--ldflags|--extension-suffix|--help|--abiflags|--configdir|--embed] == *\e\m\b\e\d* ]] +++ python-config --ldflags --embed ++ export 'PYTHONLIB=-L/usr/local/opt/python@3.11/Frameworks/Python.framework/Versions/3.11/lib/python3.11/config-3.11-darwin -lpython3.11 -ldl -framework CoreFoundation' ++ PYTHONLIB='-L/usr/local/opt/python@3.11/Frameworks/Python.framework/Versions/3.11/lib/python3.11/config-3.11-darwin -lpython3.11 -ldl -framework CoreFoundation' ++ [[ macys_VM == \m\a\c\y\s ]] ++ [[ macys_VM == \v\i\g\g\e\n ]] ++ export PYTHONUNBUFFERED=true ++ PYTHONUNBUFFERED=true ++ export PYTHONFAULTHANDLER=true ++ PYTHONFAULTHANDLER=true ++ python --version Python 3.11.5 ++ [[ '' == \D\A\R\W\I\N\6\4\.\g\c\c ]] ++ export CSMDATA=/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/data ++ CSMDATA=/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/data + unset PYTHONINC + unset PYTHONLIB + unset ESP_BLOC + unset ESP_ROOT + unset ESP_ARCH + unset AWAVE ++ uname -s + [[ Darwin == *\D\a\r\w\i\n* ]] + DESKTOP=/Users/jenkins/Desktop + OSI=macos ++ uname -m + ARCH=x86_64 + wget --tries=3 https://acdl.mit.edu/ESP/archive/ESP126-macos-x86_64.tgz --2024-07-28 00:46:28-- https://acdl.mit.edu/ESP/archive/ESP126-macos-x86_64.tgz Resolving acdl.mit.edu (acdl.mit.edu)... 18.18.33.14 Connecting to acdl.mit.edu (acdl.mit.edu)|18.18.33.14|:443... connected. HTTP request sent, awaiting response... 200 OK Length: 545954930 (521M) [application/x-gzip] Saving to: ‘ESP126-macos-x86_64.tgz’ 0K .......... .......... .......... .......... .......... 0% 6.04M 86s 50K .......... .......... .......... .......... .......... 0% 88.3M 46s 100K .......... .......... .......... .......... .......... 0% 7.39M 54s 150K .......... .......... .......... .......... .......... 0% 26.4M 46s 200K .......... .......... .......... .......... .......... 0% 19.4M 42s 250K .......... .......... .......... .......... .......... 0% 18.6M 40s 300K .......... .......... .......... .......... .......... 0% 14.7M 39s 350K .......... .......... .......... .......... .......... 0% 3.05M 55s 400K .......... .......... .......... .......... .......... 0% 30.0M 51s 450K .......... .......... .......... .......... .......... 0% 101M 47s 500K .......... .......... .......... .......... .......... 0% 126M 43s 550K .......... .......... .......... .......... .......... 0% 143M 39s 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.......... .......... .......... .......... 2% 75.1M 31s 11450K .......... .......... .......... .......... .......... 2% 32.5M 31s 11500K .......... .......... .......... .......... .......... 2% 99.2M 31s 11550K .......... .......... .......... .......... .......... 2% 64.6M 31s 11600K .......... .......... .......... .......... .......... 2% 79.4M 31s 11650K .......... .......... .......... .......... .......... 2% 128M 31s 11700K .......... .......... .......... .......... .......... 2% 109M 30s 11750K .......... .......... .......... .......... .......... 2% 9.76M 30s 11800K .......... .......... .......... .......... .......... 2% 132M 30s 11850K .......... .......... .......... .......... .......... 2% 93.0M 30s 11900K .......... .......... .......... .......... .......... 2% 105M 30s 11950K .......... .......... .......... .......... .......... 2% 57.2M 30s 12000K .......... .......... .......... .......... .......... 2% 2.68M 31s 12050K .......... .......... .......... .......... .......... 2% 55.8M 31s 12100K .......... .......... .......... .......... .......... 2% 64.5M 31s 12150K .......... .......... .......... .......... .......... 2% 110M 30s 12200K .......... .......... .......... .......... .......... 2% 89.4M 30s 12250K .......... .......... .......... .......... .......... 2% 12.9M 30s 12300K .......... .......... .......... .......... .......... 2% 119M 30s 12350K .......... .......... .......... .......... .......... 2% 112M 30s 12400K .......... .......... .......... .......... .......... 2% 132M 30s 12450K .......... .......... .......... .......... .......... 2% 106M 30s 12500K .......... .......... .......... .......... .......... 2% 70.4M 30s 12550K .......... .......... .......... .......... .......... 2% 72.9M 30s 12600K .......... .......... .......... .......... .......... 2% 70.7M 30s 12650K .......... .......... .......... .......... .......... 2% 71.7M 30s 12700K .......... .......... .......... .......... .......... 2% 91.3M 29s 12750K .......... .......... .......... .......... .......... 2% 15.3M 29s 12800K .......... .......... .......... .......... .......... 2% 107M 29s 12850K .......... .......... .......... .......... .......... 2% 105M 29s 12900K .......... .......... .......... .......... .......... 2% 88.9M 29s 12950K .......... .......... .......... .......... .......... 2% 8.06M 29s 13000K .......... .......... .......... .......... .......... 2% 72.0M 29s 13050K .......... .......... .......... .......... .......... 2% 86.7M 29s 13100K .......... .......... .......... .......... .......... 2% 10.3M 29s 13150K .......... .......... .......... .......... .......... 2% 616K 32s 13200K .......... .......... .......... .......... .......... 2% 108M 32s 13250K .......... .......... .......... .......... .......... 2% 146M 32s 13300K .......... .......... .......... .......... .......... 2% 138M 32s 13350K .......... .......... .......... .......... .......... 2% 143M 32s 13400K .......... .......... .......... .......... .......... 2% 104K 50s 13450K .......... .......... .......... .......... .......... 2% 170M 50s 13500K .......... .......... .......... .......... .......... 2% 224M 50s 13550K .......... .......... .......... .......... .......... 2% 118M 50s 13600K .......... .......... .......... .......... .......... 2% 161M 50s 13650K .......... .......... .......... .......... .......... 2% 34.9M 50s 13700K .......... .......... .......... .......... .......... 2% 155M 49s 13750K .......... .......... .......... .......... .......... 2% 159M 49s 13800K .......... .......... .......... .......... .......... 2% 84.5M 49s 13850K .......... .......... .......... .......... .......... 2% 81.7M 49s 13900K .......... .......... .......... .......... .......... 2% 114M 49s 13950K .......... .......... .......... .......... .......... 2% 146M 49s 14000K .......... .......... .......... .......... .......... 2% 162M 48s 14050K .......... .......... .......... .......... .......... 2% 173M 48s 14100K .......... .......... .......... .......... .......... 2% 178M 48s 14150K .......... .......... .......... .......... .......... 2% 206M 48s 14200K .......... .......... .......... .......... .......... 2% 181M 48s 14250K .......... .......... .......... .......... .......... 2% 182M 48s 14300K .......... .......... .......... .......... .......... 2% 156M 47s 14350K .......... .......... .......... .......... .......... 2% 153M 47s 14400K .......... .......... .......... .......... .......... 2% 209M 47s 14450K .......... .......... .......... .......... .......... 2% 158M 47s 14500K .......... .......... .......... .......... .......... 2% 210M 47s 14550K .......... .......... .......... .......... .......... 2% 216M 47s 14600K .......... .......... .......... .......... .......... 2% 38.7M 46s 14650K .......... .......... .......... .......... .......... 2% 124M 46s 14700K .......... .......... .......... .......... .......... 2% 110M 46s 14750K .......... .......... .......... .......... .......... 2% 50.7M 46s 14800K .......... .......... .......... .......... .......... 2% 5.06M 46s 14850K .......... .......... .......... .......... .......... 2% 100M 46s 14900K .......... .......... .......... .......... .......... 2% 109M 46s 14950K .......... .......... .......... .......... .......... 2% 79.3M 46s 15000K .......... .......... .......... .......... .......... 2% 120M 46s 15050K .......... .......... .......... .......... .......... 2% 170M 46s 15100K .......... .......... .......... .......... .......... 2% 7.98M 46s 15150K .......... .......... .......... .......... .......... 2% 91.6M 45s 15200K .......... .......... .......... .......... .......... 2% 73.5M 45s 15250K .......... .......... .......... .......... .......... 2% 171M 45s 15300K .......... .......... .......... .......... .......... 2% 138M 45s 15350K .......... .......... .......... .......... .......... 2% 1.34M 46s 15400K .......... .......... .......... .......... .......... 2% 149M 46s 15450K .......... .......... .......... .......... .......... 2% 133M 46s 15500K .......... .......... .......... .......... .......... 2% 32.9M 46s 15550K .......... .......... .......... .......... .......... 2% 139M 46s 15600K .......... .......... .......... .......... .......... 2% 150M 45s 15650K .......... .......... .......... .......... .......... 2% 176M 45s 15700K .......... .......... .......... .......... .......... 2% 175M 45s 15750K .......... .......... .......... .......... .......... 2% 197M 45s 15800K .......... .......... .......... .......... .......... 2% 195M 45s 15850K .......... .......... .......... .......... .......... 2% 166M 45s 15900K .......... .......... .......... .......... .......... 2% 57.7M 45s 15950K .......... .......... .......... .......... .......... 3% 140M 44s 16000K .......... .......... .......... .......... .......... 3% 119M 44s 16050K .......... .......... .......... .......... .......... 3% 188M 44s 16100K .......... .......... .......... .......... .......... 3% 153M 44s 16150K .......... .......... .......... .......... .......... 3% 141M 44s 16200K .......... .......... .......... .......... .......... 3% 153M 44s 16250K .......... .......... .......... .......... .......... 3% 182M 44s 16300K .......... .......... .......... .......... .......... 3% 61.7M 44s 16350K .......... .......... .......... .......... .......... 3% 178M 43s 16400K .......... .......... .......... .......... .......... 3% 271M 43s 16450K .......... .......... .......... .......... .......... 3% 116M 43s 16500K .......... .......... .......... .......... .......... 3% 4.56M 43s 16550K .......... .......... .......... .......... .......... 3% 150M 43s 16600K .......... .......... .......... .......... .......... 3% 162M 43s 16650K .......... .......... .......... .......... .......... 3% 185M 43s 16700K .......... .......... .......... .......... .......... 3% 122M 43s 16750K .......... .......... .......... .......... .......... 3% 189M 43s 16800K .......... .......... .......... .......... .......... 3% 4.95M 43s 16850K .......... .......... .......... .......... .......... 3% 149M 43s 16900K .......... .......... .......... .......... .......... 3% 213M 43s 16950K .......... .......... .......... .......... .......... 3% 155M 43s 17000K .......... .......... .......... .......... .......... 3% 203M 42s 17050K .......... .......... .......... .......... .......... 3% 196M 42s 17100K .......... .......... .......... .......... .......... 3% 4.84M 43s 17150K .......... .......... .......... .......... .......... 3% 180M 42s 17200K .......... .......... .......... .......... .......... 3% 184M 42s 17250K .......... .......... .......... .......... .......... 3% 182M 42s 17300K .......... .......... .......... .......... .......... 3% 161M 42s 17350K .......... .......... .......... .......... .......... 3% 101M 42s 17400K .......... .......... .......... .......... .......... 3% 1.63M 43s 17450K .......... .......... .......... .......... .......... 3% 84.8M 43s 17500K .......... .......... .......... .......... .......... 3% 157M 42s 17550K .......... .......... .......... .......... .......... 3% 152M 42s 17600K .......... .......... .......... .......... .......... 3% 176M 42s 17650K .......... .......... .......... .......... .......... 3% 209M 42s 17700K .......... .......... .......... .......... .......... 3% 145M 42s 17750K .......... .......... .......... .......... .......... 3% 174M 42s 17800K .......... .......... .......... .......... .......... 3% 217M 42s 17850K .......... .......... .......... .......... .......... 3% 145M 42s 17900K .......... .......... .......... .......... .......... 3% 187M 42s 17950K .......... .......... .......... .......... .......... 3% 132M 41s 18000K .......... .......... .......... .......... .......... 3% 175M 41s 18050K .......... .......... .......... .......... .......... 3% 192M 41s 18100K .......... .......... .......... .......... .......... 3% 147M 41s 18150K .......... .......... .......... .......... .......... 3% 174M 41s 18200K .......... .......... .......... .......... .......... 3% 160M 41s 18250K .......... .......... .......... .......... .......... 3% 174M 41s 18300K .......... .......... .......... .......... .......... 3% 303M 41s 18350K .......... .......... .......... .......... .......... 3% 15.6M 41s 18400K .......... .......... .......... .......... .......... 3% 145M 41s 18450K .......... .......... .......... .......... .......... 3% 128M 40s 18500K .......... .......... .......... .......... .......... 3% 152M 40s 18550K .......... .......... .......... .......... .......... 3% 9.12M 40s 18600K .......... .......... .......... .......... .......... 3% 155M 40s 18650K .......... .......... .......... .......... .......... 3% 167M 40s 18700K .......... .......... .......... .......... .......... 3% 5.99M 40s 18750K .......... .......... .......... .......... .......... 3% 66.6M 40s 18800K .......... .......... .......... .......... .......... 3% 77.5M 40s 18850K .......... .......... .......... .......... .......... 3% 130M 40s 18900K .......... .......... .......... .......... .......... 3% 7.53M 40s 18950K .......... .......... .......... .......... .......... 3% 72.7M 40s 19000K .......... .......... .......... .......... .......... 3% 114M 40s 19050K .......... .......... .......... .......... .......... 3% 3.32M 40s 19100K .......... .......... .......... .......... .......... 3% 144M 40s 19150K .......... .......... .......... .......... .......... 3% 216M 40s 19200K .......... .......... .......... .......... .......... 3% 186M 40s 19250K .......... .......... .......... .......... .......... 3% 210M 40s 19300K .......... .......... .......... .......... .......... 3% 136M 40s 19350K .......... .......... .......... .......... .......... 3% 160M 40s 19400K .......... .......... .......... .......... .......... 3% 206M 39s 19450K .......... .......... .......... .......... .......... 3% 443K 42s 19500K .......... .......... .......... .......... .......... 3% 167M 42s 19550K .......... .......... .......... .......... .......... 3% 120M 42s 19600K .......... .......... .......... .......... .......... 3% 144M 42s 19650K .......... .......... .......... .......... .......... 3% 63.2M 42s 19700K .......... .......... .......... .......... .......... 3% 97.3M 42s 19750K .......... .......... .......... .......... .......... 3% 38.4M 42s 19800K .......... .......... .......... .......... .......... 3% 4.75M 42s 19850K .......... .......... .......... .......... .......... 3% 25.3M 42s 19900K .......... .......... .......... .......... .......... 3% 135M 42s 19950K .......... .......... .......... .......... .......... 3% 142M 42s 20000K .......... .......... .......... .......... .......... 3% 206M 42s 20050K .......... .......... .......... .......... .......... 3% 199M 41s 20100K .......... .......... .......... .......... .......... 3% 179M 41s 20150K .......... .......... .......... .......... .......... 3% 198M 41s 20200K .......... .......... .......... .......... .......... 3% 138M 41s 20250K .......... .......... .......... .......... .......... 3% 203M 41s 20300K .......... .......... .......... .......... .......... 3% 38.7M 41s 20350K .......... .......... .......... .......... .......... 3% 61.2M 41s 20400K .......... .......... .......... .......... .......... 3% 179M 41s 20450K .......... .......... .......... .......... .......... 3% 102M 41s 20500K .......... .......... .......... .......... .......... 3% 174M 41s 20550K .......... .......... .......... .......... .......... 3% 137M 41s 20600K .......... .......... .......... .......... .......... 3% 154M 40s 20650K .......... .......... .......... .......... .......... 3% 198M 40s 20700K .......... .......... .......... .......... .......... 3% 160M 40s 20750K .......... .......... .......... .......... .......... 3% 197M 40s 20800K .......... .......... .......... .......... .......... 3% 189M 40s 20850K .......... .......... .......... .......... .......... 3% 165M 40s 20900K .......... .......... .......... .......... .......... 3% 132M 40s 20950K .......... .......... .......... .......... .......... 3% 176M 40s 21000K .......... .......... .......... .......... .......... 3% 7.17M 40s 21050K .......... .......... .......... .......... .......... 3% 81.1M 40s 21100K .......... .......... .......... .......... .......... 3% 108M 40s 21150K .......... .......... .......... .......... .......... 3% 127M 40s 21200K .......... .......... .......... .......... .......... 3% 139M 40s 21250K .......... .......... .......... .......... .......... 3% 138M 39s 21300K .......... .......... .......... .......... .......... 4% 135M 39s 21350K .......... .......... .......... .......... .......... 4% 7.29M 39s 21400K .......... .......... .......... .......... .......... 4% 127M 39s 21450K .......... .......... .......... .......... .......... 4% 170M 39s 21500K .......... .......... .......... .......... .......... 4% 3.07M 40s 21550K .......... .......... .......... .......... .......... 4% 125M 39s 21600K .......... .......... .......... .......... .......... 4% 94.4M 39s 21650K .......... .......... .......... .......... .......... 4% 133M 39s 21700K .......... .......... .......... .......... .......... 4% 114M 39s 21750K .......... .......... .......... .......... .......... 4% 157M 39s 21800K .......... .......... .......... .......... .......... 4% 176M 39s 21850K .......... .......... .......... .......... .......... 4% 170M 39s 21900K .......... .......... .......... .......... .......... 4% 184M 39s 21950K .......... .......... .......... .......... .......... 4% 155M 39s 22000K .......... .......... .......... .......... .......... 4% 5.13M 39s 22050K .......... .......... .......... .......... .......... 4% 90.4M 39s 22100K .......... .......... .......... .......... .......... 4% 132M 39s 22150K .......... .......... .......... .......... .......... 4% 150M 39s 22200K .......... .......... .......... .......... .......... 4% 164M 39s 22250K .......... .......... .......... .......... .......... 4% 2.44M 39s 22300K .......... .......... .......... .......... .......... 4% 169M 39s 22350K .......... .......... .......... .......... .......... 4% 95.6M 39s 22400K .......... .......... .......... .......... .......... 4% 5.85M 39s 22450K .......... .......... .......... .......... .......... 4% 65.0M 39s 22500K .......... .......... .......... .......... .......... 4% 111M 39s 22550K .......... .......... .......... .......... .......... 4% 94.3M 39s 22600K .......... .......... .......... .......... .......... 4% 97.1M 39s 22650K .......... .......... .......... .......... .......... 4% 167M 38s 22700K .......... .......... .......... .......... .......... 4% 128M 38s 22750K .......... .......... .......... .......... .......... 4% 28.2M 38s 22800K .......... .......... .......... .......... .......... 4% 119M 38s 22850K .......... .......... .......... .......... .......... 4% 3.91M 38s 22900K .......... .......... .......... .......... .......... 4% 82.8M 38s 22950K .......... .......... .......... .......... .......... 4% 112M 38s 23000K .......... .......... .......... .......... .......... 4% 59.8M 38s 23050K .......... .......... .......... .......... .......... 4% 77.9M 38s 23100K .......... .......... .......... .......... .......... 4% 95.9M 38s 23150K .......... .......... .......... .......... .......... 4% 112M 38s 23200K .......... .......... .......... .......... .......... 4% 111M 38s 23250K .......... .......... .......... .......... .......... 4% 7.00M 38s 23300K .......... .......... .......... .......... .......... 4% 173M 38s 23350K .......... .......... .......... .......... .......... 4% 150M 38s 23400K .......... .......... .......... .......... .......... 4% 226M 38s 23450K .......... .......... .......... .......... .......... 4% 178M 38s 23500K .......... .......... .......... .......... .......... 4% 11.9M 38s 23550K .......... .......... .......... .......... .......... 4% 95.4K 49s 23600K .......... .......... .......... .......... .......... 4% 131M 49s 23650K .......... .......... .......... .......... .......... 4% 186M 49s 23700K .......... .......... .......... .......... .......... 4% 59.3M 49s 23750K .......... .......... .......... .......... .......... 4% 57.0M 49s 23800K .......... .......... .......... .......... .......... 4% 74.2M 48s 23850K .......... .......... .......... .......... .......... 4% 79.9M 48s 23900K .......... .......... .......... .......... .......... 4% 169M 48s 23950K .......... .......... .......... .......... .......... 4% 156M 48s 24000K .......... .......... .......... .......... .......... 4% 127M 48s 24050K .......... .......... .......... .......... .......... 4% 133M 48s 24100K .......... .......... .......... .......... .......... 4% 127M 48s 24150K .......... .......... .......... .......... .......... 4% 134M 48s 24200K .......... .......... .......... .......... .......... 4% 185M 48s 24250K .......... .......... .......... .......... .......... 4% 191M 48s 24300K .......... .......... .......... .......... .......... 4% 162M 47s 24350K .......... .......... .......... .......... .......... 4% 95.7M 47s 24400K .......... .......... .......... .......... .......... 4% 137M 47s 24450K .......... .......... .......... .......... .......... 4% 161M 47s 24500K .......... .......... .......... .......... .......... 4% 196M 47s 24550K .......... .......... .......... .......... .......... 4% 32.7M 47s 24600K .......... .......... .......... .......... .......... 4% 110M 47s 24650K .......... .......... .......... .......... .......... 4% 104M 47s 24700K .......... .......... .......... .......... .......... 4% 60.1M 47s 24750K .......... .......... .......... .......... .......... 4% 5.06M 47s 24800K .......... .......... .......... .......... .......... 4% 206M 47s 24850K .......... .......... .......... .......... .......... 4% 98.8M 47s 24900K .......... .......... .......... .......... .......... 4% 159M 47s 24950K .......... .......... .......... .......... .......... 4% 156M 46s 25000K .......... .......... .......... .......... .......... 4% 51.3M 46s 25050K .......... .......... .......... .......... .......... 4% 150M 46s 25100K .......... .......... .......... .......... .......... 4% 4.30M 46s 25150K .......... .......... .......... .......... .......... 4% 147M 46s 25200K .......... .......... .......... .......... .......... 4% 107M 46s 25250K .......... .......... .......... .......... .......... 4% 112M 46s 25300K .......... .......... .......... .......... .......... 4% 71.9M 46s 25350K .......... .......... .......... .......... .......... 4% 176M 46s 25400K .......... .......... .......... .......... .......... 4% 186M 46s 25450K .......... .......... .......... .......... .......... 4% 160M 46s 25500K .......... .......... .......... .......... .......... 4% 1.24M 47s 25550K .......... .......... .......... .......... .......... 4% 168M 46s 25600K .......... .......... .......... .......... .......... 4% 469K 48s 25650K .......... .......... .......... .......... .......... 4% 185M 48s 25700K .......... .......... .......... .......... .......... 4% 7.32M 48s 25750K .......... .......... .......... .......... .......... 4% 206M 48s 25800K .......... .......... .......... .......... .......... 4% 216M 48s 25850K .......... .......... .......... .......... .......... 4% 182M 48s 25900K .......... .......... .......... .......... .......... 4% 27.9M 48s 25950K .......... .......... .......... .......... .......... 4% 113M 48s 26000K .......... .......... .......... .......... .......... 4% 155M 48s 26050K .......... .......... .......... .......... .......... 4% 167M 48s 26100K .......... .......... .......... .......... .......... 4% 151M 48s 26150K .......... .......... .......... .......... .......... 4% 183M 48s 26200K .......... .......... .......... .......... .......... 4% 74.2M 48s 26250K .......... .......... .......... .......... .......... 4% 86.6M 47s 26300K .......... .......... .......... .......... .......... 4% 64.5M 47s 26350K .......... .......... .......... .......... .......... 4% 157M 47s 26400K .......... .......... .......... .......... .......... 4% 190M 47s 26450K .......... .......... .......... .......... .......... 4% 173M 47s 26500K .......... .......... .......... .......... .......... 4% 3.36M 47s 26550K .......... .......... .......... .......... .......... 4% 202M 47s 26600K .......... .......... .......... .......... .......... 4% 149M 47s 26650K .......... .......... .......... .......... .......... 5% 221M 47s 26700K .......... .......... .......... .......... .......... 5% 108M 47s 26750K .......... .......... .......... .......... .......... 5% 99.0M 47s 26800K .......... .......... .......... .......... .......... 5% 223M 47s 26850K .......... .......... .......... .......... .......... 5% 195M 47s 26900K .......... .......... .......... .......... .......... 5% 229M 47s 26950K .......... .......... .......... .......... .......... 5% 137M 46s 27000K .......... .......... .......... .......... .......... 5% 144M 46s 27050K .......... .......... .......... .......... .......... 5% 171M 46s 27100K .......... .......... .......... .......... .......... 5% 121M 46s 27150K .......... .......... .......... .......... .......... 5% 199M 46s 27200K .......... .......... .......... .......... .......... 5% 2.28M 46s 27250K .......... .......... .......... .......... .......... 5% 210M 46s 27300K .......... .......... .......... .......... .......... 5% 171M 46s 27350K .......... .......... .......... .......... .......... 5% 178M 46s 27400K .......... .......... .......... .......... .......... 5% 216M 46s 27450K .......... .......... .......... .......... .......... 5% 146M 46s 27500K .......... .......... 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5% 155M 45s 28200K .......... .......... .......... .......... .......... 5% 126M 45s 28250K .......... .......... .......... .......... .......... 5% 8.90M 45s 28300K .......... .......... .......... .......... .......... 5% 47.5M 45s 28350K .......... .......... .......... .......... .......... 5% 154M 45s 28400K .......... .......... .......... .......... .......... 5% 61.4M 45s 28450K .......... .......... .......... .......... .......... 5% 8.87M 45s 28500K .......... .......... .......... .......... .......... 5% 138M 45s 28550K .......... .......... .......... .......... .......... 5% 211M 45s 28600K .......... .......... .......... .......... .......... 5% 109M 45s 28650K .......... .......... .......... .......... .......... 5% 480K 46s 28700K .......... .......... .......... .......... .......... 5% 18.0M 46s 28750K .......... .......... .......... .......... .......... 5% 119M 46s 28800K .......... .......... .......... .......... .......... 5% 180M 46s 28850K .......... .......... .......... .......... .......... 5% 62.9M 46s 28900K .......... .......... .......... .......... .......... 5% 78.6M 46s 28950K .......... .......... .......... .......... .......... 5% 35.5M 46s 29000K .......... .......... .......... .......... .......... 5% 42.6M 46s 29050K .......... .......... .......... .......... .......... 5% 37.6M 46s 29100K .......... .......... .......... .......... .......... 5% 16.9M 46s 29150K .......... .......... .......... .......... .......... 5% 97.1M 46s 29200K .......... .......... .......... .......... .......... 5% 37.4M 46s 29250K .......... .......... .......... .......... .......... 5% 42.6M 46s 29300K .......... .......... .......... .......... .......... 5% 51.7M 46s 29350K .......... .......... .......... .......... .......... 5% 74.2M 46s 29400K .......... .......... .......... .......... .......... 5% 50.0M 45s 29450K .......... .......... .......... .......... .......... 5% 59.7M 45s 29500K .......... .......... .......... 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59s 30200K .......... .......... .......... .......... .......... 5% 146M 59s 30250K .......... .......... .......... .......... .......... 5% 140M 59s 30300K .......... .......... .......... .......... .......... 5% 163M 59s 30350K .......... .......... .......... .......... .......... 5% 114M 58s 30400K .......... .......... .......... .......... .......... 5% 109M 58s 30450K .......... .......... .......... .......... .......... 5% 15.1M 58s 30500K .......... .......... .......... .......... .......... 5% 127M 58s 30550K .......... .......... .......... .......... .......... 5% 124M 58s 30600K .......... .......... .......... .......... .......... 5% 75.6M 58s 30650K .......... .......... .......... .......... .......... 5% 114M 58s 30700K .......... .......... .......... .......... .......... 5% 1.41M 58s 30750K .......... .......... .......... .......... .......... 5% 37.8M 58s 30800K .......... .......... .......... .......... .......... 5% 138M 58s 30850K .......... .......... 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5% 122M 57s 31550K .......... .......... .......... .......... .......... 5% 210M 57s 31600K .......... .......... .......... .......... .......... 5% 200M 57s 31650K .......... .......... .......... .......... .......... 5% 221M 57s 31700K .......... .......... .......... .......... .......... 5% 116M 57s 31750K .......... .......... .......... .......... .......... 5% 164M 56s 31800K .......... .......... .......... .......... .......... 5% 111M 56s 31850K .......... .......... .......... .......... .......... 5% 181M 56s 31900K .......... .......... .......... .......... .......... 5% 9.13M 56s 31950K .......... .......... .......... .......... .......... 6% 84.6M 56s 32000K .......... .......... .......... .......... .......... 6% 139M 56s 32050K .......... .......... .......... .......... .......... 6% 214M 56s 32100K .......... .......... .......... .......... .......... 6% 176M 56s 32150K .......... .......... .......... .......... .......... 6% 224M 56s 32200K .......... 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.......... 6% 168M 56s 32900K .......... .......... .......... .......... .......... 6% 205M 56s 32950K .......... .......... .......... .......... .......... 6% 172M 56s 33000K .......... .......... .......... .......... .......... 6% 58.9M 56s 33050K .......... .......... .......... .......... .......... 6% 117M 55s 33100K .......... .......... .......... .......... .......... 6% 49.2M 55s 33150K .......... .......... .......... .......... .......... 6% 186M 55s 33200K .......... .......... .......... .......... .......... 6% 176M 55s 33250K .......... .......... .......... .......... .......... 6% 208M 55s 33300K .......... .......... .......... .......... .......... 6% 208M 55s 33350K .......... .......... .......... .......... .......... 6% 191M 55s 33400K .......... .......... .......... .......... .......... 6% 197M 55s 33450K .......... .......... .......... .......... .......... 6% 141M 55s 33500K .......... .......... .......... .......... .......... 6% 171M 55s 33550K 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34900K .......... .......... .......... .......... .......... 6% 151M 53s 34950K .......... .......... .......... .......... .......... 6% 158M 53s 35000K .......... .......... .......... .......... .......... 6% 161M 53s 35050K .......... .......... .......... .......... .......... 6% 168M 53s 35100K .......... .......... .......... .......... .......... 6% 161M 53s 35150K .......... .......... .......... .......... .......... 6% 137M 53s 35200K .......... .......... .......... .......... .......... 6% 146M 53s 35250K .......... .......... .......... .......... .......... 6% 162M 53s 35300K .......... .......... .......... .......... .......... 6% 6.63M 53s 35350K .......... .......... .......... .......... .......... 6% 182M 52s 35400K .......... .......... .......... .......... .......... 6% 183M 52s 35450K .......... .......... .......... .......... .......... 6% 128M 52s 35500K .......... .......... .......... .......... .......... 6% 158M 52s 35550K .......... .......... 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7% 225M 51s 38250K .......... .......... .......... .......... .......... 7% 289M 51s 38300K .......... .......... .......... .......... .......... 7% 274M 51s 38350K .......... .......... .......... .......... .......... 7% 192M 51s 38400K .......... .......... .......... .......... .......... 7% 208M 51s 38450K .......... .......... .......... .......... .......... 7% 78.4M 51s 38500K .......... .......... .......... .......... .......... 7% 95.7M 50s 38550K .......... .......... .......... .......... .......... 7% 120M 50s 38600K .......... .......... .......... .......... .......... 7% 42.8M 50s 38650K .......... .......... .......... .......... .......... 7% 208M 50s 38700K .......... .......... .......... .......... .......... 7% 178M 50s 38750K .......... .......... .......... .......... .......... 7% 211M 50s 38800K .......... .......... .......... .......... .......... 7% 195M 50s 38850K .......... .......... .......... .......... .......... 7% 176M 50s 38900K .......... 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.......... .......... 7% 305M 49s 40950K .......... .......... .......... .......... .......... 7% 268K 51s 41000K .......... .......... .......... .......... .......... 7% 23.7M 51s 41050K .......... .......... .......... .......... .......... 7% 109M 51s 41100K .......... .......... .......... .......... .......... 7% 173M 51s 41150K .......... .......... .......... .......... .......... 7% 26.2M 51s 41200K .......... .......... .......... .......... .......... 7% 114M 51s 41250K .......... .......... .......... .......... .......... 7% 170M 51s 41300K .......... .......... .......... .......... .......... 7% 46.6M 51s 41350K .......... .......... .......... .......... .......... 7% 133M 51s 41400K .......... .......... .......... .......... .......... 7% 244M 51s 41450K .......... .......... .......... .......... .......... 7% 212M 51s 41500K .......... .......... .......... .......... .......... 7% 124M 50s 41550K .......... .......... .......... .......... .......... 7% 97.1M 50s 41600K .......... .......... .......... .......... .......... 7% 110M 50s 41650K .......... .......... .......... .......... .......... 7% 97.5M 50s 41700K .......... .......... .......... .......... .......... 7% 205M 50s 41750K .......... .......... .......... .......... .......... 7% 189M 50s 41800K .......... .......... .......... .......... .......... 7% 26.8M 50s 41850K .......... .......... .......... .......... .......... 7% 92.0M 50s 41900K .......... .......... .......... .......... .......... 7% 146M 50s 41950K .......... .......... .......... .......... .......... 7% 36.2M 50s 42000K .......... .......... .......... .......... .......... 7% 145M 50s 42050K .......... .......... .......... .......... .......... 7% 26.3M 50s 42100K .......... .......... .......... .......... .......... 7% 138M 50s 42150K .......... .......... .......... .......... .......... 7% 50.7M 50s 42200K .......... .......... .......... .......... .......... 7% 115M 50s 42250K .......... .......... .......... .......... .......... 7% 134M 50s 42300K .......... .......... .......... .......... .......... 7% 175M 50s 42350K .......... .......... .......... .......... .......... 7% 108M 50s 42400K .......... .......... .......... .......... .......... 7% 153M 49s 42450K .......... .......... .......... .......... .......... 7% 8.12M 49s 42500K .......... .......... .......... .......... .......... 7% 118M 49s 42550K .......... .......... .......... .......... .......... 7% 139M 49s 42600K .......... .......... .......... .......... .......... 7% 101M 49s 42650K .......... .......... .......... .......... .......... 8% 150M 49s 42700K .......... .......... .......... .......... .......... 8% 6.39M 49s 42750K .......... .......... .......... .......... .......... 8% 97.1M 49s 42800K .......... .......... .......... .......... .......... 8% 203M 49s 42850K .......... .......... .......... .......... .......... 8% 156M 49s 42900K .......... .......... .......... .......... .......... 8% 119M 49s 42950K .......... .......... .......... .......... .......... 8% 26.4M 49s 43000K .......... .......... .......... .......... .......... 8% 263K 51s 43050K .......... .......... .......... .......... .......... 8% 210M 51s 43100K .......... .......... .......... .......... .......... 8% 24.9M 51s 43150K .......... .......... .......... .......... .......... 8% 118M 51s 43200K .......... .......... .......... .......... .......... 8% 89.6M 51s 43250K .......... .......... .......... .......... .......... 8% 102M 51s 43300K .......... .......... .......... .......... .......... 8% 69.9M 51s 43350K .......... .......... .......... .......... .......... 8% 111M 51s 43400K .......... .......... .......... .......... .......... 8% 174M 51s 43450K .......... .......... .......... .......... .......... 8% 105M 51s 43500K .......... .......... .......... .......... .......... 8% 27.0M 51s 43550K .......... .......... .......... .......... .......... 8% 169M 50s 43600K .......... 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.......... 8% 190M 50s 44300K .......... .......... .......... .......... .......... 8% 209M 50s 44350K .......... .......... .......... .......... .......... 8% 28.8M 50s 44400K .......... .......... .......... .......... .......... 8% 208M 50s 44450K .......... .......... .......... .......... .......... 8% 196M 49s 44500K .......... .......... .......... .......... .......... 8% 29.7M 49s 44550K .......... .......... .......... .......... .......... 8% 160M 49s 44600K .......... .......... .......... .......... .......... 8% 87.0M 49s 44650K .......... .......... .......... .......... .......... 8% 192M 49s 44700K .......... .......... .......... .......... .......... 8% 29.7M 49s 44750K .......... .......... .......... .......... .......... 8% 111M 49s 44800K .......... .......... .......... .......... .......... 8% 7.03M 49s 44850K .......... .......... .......... .......... .......... 8% 111M 49s 44900K .......... .......... .......... .......... .......... 8% 142M 49s 44950K 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46300K .......... .......... .......... .......... .......... 8% 144M 49s 46350K .......... .......... .......... .......... .......... 8% 24.4M 49s 46400K .......... .......... .......... .......... .......... 8% 29.0M 49s 46450K .......... .......... .......... .......... .......... 8% 17.0M 49s 46500K .......... .......... .......... .......... .......... 8% 112M 49s 46550K .......... .......... .......... .......... .......... 8% 157M 49s 46600K .......... .......... .......... .......... .......... 8% 138M 49s 46650K .......... .......... .......... .......... .......... 8% 177M 49s 46700K .......... .......... .......... .......... .......... 8% 172M 49s 46750K .......... .......... .......... .......... .......... 8% 189M 49s 46800K .......... .......... .......... .......... .......... 8% 165M 49s 46850K .......... .......... .......... .......... .......... 8% 155M 49s 46900K .......... .......... .......... .......... .......... 8% 195M 49s 46950K .......... .......... 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8% 127M 48s 47650K .......... .......... .......... .......... .......... 8% 180M 48s 47700K .......... .......... .......... .......... .......... 8% 114M 48s 47750K .......... .......... .......... .......... .......... 8% 56.8M 48s 47800K .......... .......... .......... .......... .......... 8% 8.20M 48s 47850K .......... .......... .......... .......... .......... 8% 141M 48s 47900K .......... .......... .......... .......... .......... 8% 114M 48s 47950K .......... .......... .......... .......... .......... 9% 58.5M 48s 48000K .......... .......... .......... .......... .......... 9% 180M 48s 48050K .......... .......... .......... .......... .......... 9% 6.67M 48s 48100K .......... .......... .......... .......... .......... 9% 532K 49s 48150K .......... .......... .......... .......... .......... 9% 56.1M 49s 48200K .......... .......... .......... .......... .......... 9% 43.8M 49s 48250K .......... .......... .......... .......... .......... 9% 110M 48s 48300K .......... 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.......... .......... 10% 214M 44s 55700K .......... .......... .......... .......... .......... 10% 198M 44s 55750K .......... .......... .......... .......... .......... 10% 6.57M 44s 55800K .......... .......... .......... .......... .......... 10% 172M 44s 55850K .......... .......... .......... .......... .......... 10% 118M 44s 55900K .......... .......... .......... .......... .......... 10% 79.7M 44s 55950K .......... .......... .......... .......... .......... 10% 187M 44s 56000K .......... .......... .......... .......... .......... 10% 5.92M 44s 56050K .......... .......... .......... .......... .......... 10% 105M 44s 56100K .......... .......... .......... .......... .......... 10% 181M 44s 56150K .......... .......... .......... .......... .......... 10% 89.4M 44s 56200K .......... .......... .......... .......... .......... 10% 145M 44s 56250K .......... .......... .......... .......... .......... 10% 163M 44s 56300K .......... .......... .......... .......... .......... 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110M 39s 72200K .......... .......... .......... .......... .......... 13% 12.6M 39s 72250K .......... .......... .......... .......... .......... 13% 80.3M 39s 72300K .......... .......... .......... .......... .......... 13% 6.05M 39s 72350K .......... .......... .......... .......... .......... 13% 86.4M 39s 72400K .......... .......... .......... .......... .......... 13% 152M 39s 72450K .......... .......... .......... .......... .......... 13% 184M 39s 72500K .......... .......... .......... .......... .......... 13% 217M 39s 72550K .......... .......... .......... .......... .......... 13% 210M 39s 72600K .......... .......... .......... .......... .......... 13% 96.7M 39s 72650K .......... .......... .......... .......... .......... 13% 5.51M 39s 72700K .......... .......... .......... .......... .......... 13% 527K 40s 72750K .......... .......... .......... .......... .......... 13% 19.8M 40s 72800K .......... .......... .......... .......... .......... 13% 13.9M 40s 72850K 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86750K .......... .......... .......... .......... .......... 16% 212M 36s 86800K .......... .......... .......... .......... .......... 16% 6.83M 36s 86850K .......... .......... .......... .......... .......... 16% 106M 36s 86900K .......... .......... .......... .......... .......... 16% 124M 36s 86950K .......... .......... .......... .......... .......... 16% 87.2M 36s 87000K .......... .......... .......... .......... .......... 16% 764K 37s 87050K .......... .......... .......... .......... .......... 16% 61.6M 37s 87100K .......... .......... .......... .......... .......... 16% 22.8M 37s 87150K .......... .......... .......... .......... .......... 16% 93.0M 37s 87200K .......... .......... .......... .......... .......... 16% 73.5M 37s 87250K .......... .......... .......... .......... .......... 16% 48.6M 37s 87300K .......... .......... .......... .......... .......... 16% 84.8M 37s 87350K .......... .......... .......... .......... .......... 16% 50.7M 37s 87400K 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39s 90700K .......... .......... .......... .......... .......... 17% 138M 39s 90750K .......... .......... .......... .......... .......... 17% 292M 39s 90800K .......... .......... .......... .......... .......... 17% 8.73M 39s 90850K .......... .......... .......... .......... .......... 17% 92.1M 39s 90900K .......... .......... .......... .......... .......... 17% 41.9M 39s 90950K .......... .......... .......... .......... .......... 17% 112M 39s 91000K .......... .......... .......... .......... .......... 17% 172M 39s 91050K .......... .......... .......... .......... .......... 17% 56.0M 39s 91100K .......... .......... .......... .......... .......... 17% 3.81M 39s 91150K .......... .......... .......... .......... .......... 17% 140M 39s 91200K .......... .......... .......... .......... .......... 17% 129M 39s 91250K .......... .......... .......... .......... .......... 17% 130M 39s 91300K .......... .......... .......... .......... .......... 17% 95.2M 39s 91350K 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.......... .......... 18% 5.70M 38s 96000K .......... .......... .......... .......... .......... 18% 152M 38s 96050K .......... .......... .......... .......... .......... 18% 158M 38s 96100K .......... .......... .......... .......... .......... 18% 89.8M 38s 96150K .......... .......... .......... .......... .......... 18% 127M 38s 96200K .......... .......... .......... .......... .......... 18% 117M 38s 96250K .......... .......... .......... .......... .......... 18% 296K 39s 96300K .......... .......... .......... .......... .......... 18% 60.7M 39s 96350K .......... .......... .......... .......... .......... 18% 149M 39s 96400K .......... .......... .......... .......... .......... 18% 159M 38s 96450K .......... .......... .......... .......... .......... 18% 162M 38s 96500K .......... .......... .......... .......... .......... 18% 198M 38s 96550K .......... .......... .......... .......... .......... 18% 42.5M 38s 96600K .......... .......... .......... .......... .......... 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.......... .......... 18% 125M 38s 99300K .......... .......... .......... .......... .......... 18% 3.74M 38s 99350K .......... .......... .......... .......... .......... 18% 1.13M 38s 99400K .......... .......... .......... .......... .......... 18% 3.94M 38s 99450K .......... .......... .......... .......... .......... 18% 16.3M 38s 99500K .......... .......... .......... .......... .......... 18% 10.1M 38s 99550K .......... .......... .......... .......... .......... 18% 16.9M 38s 99600K .......... .......... .......... .......... .......... 18% 73.1M 38s 99650K .......... .......... .......... .......... .......... 18% 23.1M 38s 99700K .......... .......... .......... .......... .......... 18% 7.64M 38s 99750K .......... .......... .......... .......... .......... 18% 7.52M 38s 99800K .......... .......... .......... .......... .......... 18% 4.72M 38s 99850K .......... .......... .......... .......... .......... 18% 16.1M 38s 99900K .......... .......... .......... .......... .......... 18% 1.44M 38s 99950K .......... .......... .......... .......... .......... 18% 93.2M 38s 100000K .......... .......... .......... .......... .......... 18% 189M 38s 100050K .......... .......... .......... .......... .......... 18% 39.8M 38s 100100K .......... .......... .......... .......... .......... 18% 8.48M 38s 100150K .......... .......... .......... .......... .......... 18% 34.7M 38s 100200K .......... .......... .......... .......... .......... 18% 32.9M 38s 100250K .......... .......... .......... .......... .......... 18% 39.8M 38s 100300K .......... .......... .......... .......... .......... 18% 6.68M 38s 100350K .......... .......... .......... .......... .......... 18% 15.5M 38s 100400K .......... .......... .......... .......... .......... 18% 123M 38s 100450K .......... .......... .......... .......... .......... 18% 157M 38s 100500K .......... .......... .......... .......... .......... 18% 68.6M 38s 100550K .......... .......... .......... .......... .......... 18% 35.0M 38s 100600K .......... .......... .......... .......... .......... 18% 147M 38s 100650K .......... .......... .......... .......... .......... 18% 205M 38s 100700K .......... .......... .......... .......... .......... 18% 151M 38s 100750K .......... .......... .......... .......... .......... 18% 11.8M 38s 100800K .......... .......... .......... .......... .......... 18% 84.5M 38s 100850K .......... .......... .......... .......... .......... 18% 128M 38s 100900K .......... .......... .......... .......... .......... 18% 170M 38s 100950K .......... .......... .......... .......... .......... 18% 128M 38s 101000K .......... .......... .......... .......... .......... 18% 50.1M 38s 101050K .......... .......... .......... .......... .......... 18% 176M 38s 101100K .......... .......... .......... .......... .......... 18% 144M 38s 101150K .......... .......... .......... .......... .......... 18% 189M 38s 101200K .......... .......... .......... .......... .......... 18% 142M 38s 101250K .......... .......... .......... .......... .......... 18% 178M 38s 101300K .......... .......... .......... .......... .......... 19% 24.2M 38s 101350K .......... .......... .......... .......... .......... 19% 6.50M 38s 101400K .......... .......... .......... .......... .......... 19% 29.0M 38s 101450K .......... .......... .......... .......... .......... 19% 78.5M 38s 101500K .......... .......... .......... .......... .......... 19% 25.6M 38s 101550K .......... .......... .......... .......... .......... 19% 109M 38s 101600K .......... .......... .......... .......... .......... 19% 14.3M 38s 101650K .......... .......... .......... .......... .......... 19% 104M 38s 101700K .......... .......... .......... .......... .......... 19% 142M 37s 101750K .......... .......... .......... .......... .......... 19% 102M 37s 101800K .......... .......... .......... .......... .......... 19% 162M 37s 101850K .......... .......... .......... .......... .......... 19% 21.7M 37s 101900K .......... .......... .......... .......... .......... 19% 78.9M 37s 101950K .......... .......... .......... .......... .......... 19% 67.3M 37s 102000K .......... .......... .......... .......... .......... 19% 77.9M 37s 102050K .......... .......... .......... .......... .......... 19% 66.1M 37s 102100K .......... .......... .......... .......... .......... 19% 74.8M 37s 102150K .......... .......... .......... .......... .......... 19% 91.1M 37s 102200K .......... .......... .......... .......... .......... 19% 95.6M 37s 102250K .......... .......... .......... .......... .......... 19% 166M 37s 102300K .......... .......... .......... .......... .......... 19% 109M 37s 102350K .......... .......... .......... .......... .......... 19% 130M 37s 102400K .......... .......... .......... .......... .......... 19% 1.68M 37s 102450K .......... .......... .......... .......... .......... 19% 72.9M 37s 102500K .......... .......... .......... .......... 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.......... 21% 5.99M 36s 113600K .......... .......... .......... .......... .......... 21% 101M 36s 113650K .......... .......... .......... .......... .......... 21% 3.09M 36s 113700K .......... .......... .......... .......... .......... 21% 31.0M 36s 113750K .......... .......... .......... .......... .......... 21% 38.3M 36s 113800K .......... .......... .......... .......... .......... 21% 95.7M 36s 113850K .......... .......... .......... .......... .......... 21% 89.8M 36s 113900K .......... .......... .......... .......... .......... 21% 130M 36s 113950K .......... .......... .......... .......... .......... 21% 37.1M 36s 114000K .......... .......... .......... .......... .......... 21% 52.9M 36s 114050K .......... .......... .......... .......... .......... 21% 45.8M 36s 114100K .......... .......... .......... .......... .......... 21% 94.1M 36s 114150K .......... .......... .......... .......... .......... 21% 126M 36s 114200K .......... .......... .......... .......... .......... 21% 72.0M 36s 114250K .......... .......... .......... .......... .......... 21% 128M 36s 114300K .......... .......... .......... .......... .......... 21% 104M 36s 114350K .......... .......... .......... .......... .......... 21% 27.4M 36s 114400K .......... .......... .......... .......... .......... 21% 160M 36s 114450K .......... .......... .......... .......... .......... 21% 67.6M 36s 114500K .......... .......... .......... .......... .......... 21% 230M 36s 114550K .......... .......... .......... .......... .......... 21% 133M 36s 114600K .......... .......... .......... .......... .......... 21% 53.9M 36s 114650K .......... .......... .......... .......... .......... 21% 21.6M 36s 114700K .......... .......... .......... .......... .......... 21% 2.35M 36s 114750K .......... .......... .......... .......... .......... 21% 2.00M 36s 114800K .......... .......... .......... .......... .......... 21% 9.38M 36s 114850K .......... .......... .......... .......... .......... 21% 178M 36s 114900K .......... .......... .......... .......... .......... 21% 114M 36s 114950K .......... .......... .......... .......... .......... 21% 121M 36s 115000K .......... .......... .......... .......... .......... 21% 101M 36s 115050K .......... .......... .......... .......... .......... 21% 39.8M 36s 115100K .......... .......... .......... .......... .......... 21% 3.79M 36s 115150K .......... .......... .......... .......... .......... 21% 14.8M 36s 115200K .......... .......... .......... .......... .......... 21% 38.4M 36s 115250K .......... .......... .......... .......... .......... 21% 80.0M 36s 115300K .......... .......... .......... .......... .......... 21% 13.9M 36s 115350K .......... .......... .......... .......... .......... 21% 27.6M 36s 115400K .......... .......... .......... .......... .......... 21% 67.5M 36s 115450K .......... .......... .......... .......... .......... 21% 18.4M 36s 115500K .......... .......... .......... .......... .......... 21% 67.9M 36s 115550K .......... .......... .......... .......... .......... 21% 65.6M 36s 115600K .......... .......... .......... .......... .......... 21% 10.5M 36s 115650K .......... .......... .......... .......... .......... 21% 5.55M 36s 115700K .......... .......... .......... .......... .......... 21% 5.68M 36s 115750K .......... .......... .......... .......... .......... 21% 57.2M 36s 115800K .......... .......... .......... .......... .......... 21% 29.5M 36s 115850K .......... .......... .......... .......... .......... 21% 5.10M 36s 115900K .......... .......... .......... .......... .......... 21% 52.6M 36s 115950K .......... .......... .......... .......... .......... 21% 66.0M 36s 116000K .......... .......... .......... .......... .......... 21% 170M 36s 116050K .......... .......... .......... .......... .......... 21% 65.5M 36s 116100K .......... .......... .......... .......... .......... 21% 87.7M 36s 116150K .......... .......... .......... .......... .......... 21% 41.3M 36s 116200K .......... .......... .......... .......... .......... 21% 31.9M 36s 116250K .......... .......... .......... .......... .......... 21% 14.9M 36s 116300K .......... .......... .......... .......... .......... 21% 73.9M 36s 116350K .......... .......... .......... .......... .......... 21% 118M 36s 116400K .......... .......... .......... .......... .......... 21% 28.6M 36s 116450K .......... .......... .......... .......... .......... 21% 54.4M 36s 116500K .......... .......... .......... .......... .......... 21% 64.1M 36s 116550K .......... .......... .......... .......... .......... 21% 54.9M 36s 116600K .......... .......... .......... .......... .......... 21% 76.4M 36s 116650K .......... .......... .......... .......... .......... 21% 86.0M 36s 116700K .......... .......... .......... .......... .......... 21% 42.6M 36s 116750K .......... .......... .......... .......... .......... 21% 108M 36s 116800K .......... .......... .......... .......... .......... 21% 164M 35s 116850K .......... .......... .......... .......... .......... 21% 60.6M 35s 116900K .......... .......... .......... .......... .......... 21% 95.0M 35s 116950K .......... .......... .......... .......... .......... 21% 93.2M 35s 117000K .......... .......... .......... .......... .......... 21% 22.4M 35s 117050K .......... .......... .......... .......... .......... 21% 31.7M 35s 117100K .......... .......... .......... .......... .......... 21% 82.9M 35s 117150K .......... .......... .......... .......... .......... 21% 58.7M 35s 117200K .......... .......... .......... .......... .......... 21% 52.0M 35s 117250K .......... .......... .......... .......... .......... 22% 8.92M 35s 117300K .......... .......... .......... .......... .......... 22% 27.0M 35s 117350K .......... .......... .......... .......... .......... 22% 51.8M 35s 117400K .......... .......... .......... .......... .......... 22% 46.5M 35s 117450K .......... .......... .......... .......... .......... 22% 87.5M 35s 117500K .......... .......... .......... .......... .......... 22% 97.7M 35s 117550K .......... .......... .......... .......... .......... 22% 66.5M 35s 117600K .......... .......... .......... .......... .......... 22% 114M 35s 117650K .......... .......... .......... .......... .......... 22% 31.9M 35s 117700K .......... .......... .......... .......... .......... 22% 7.31M 35s 117750K .......... .......... .......... .......... .......... 22% 2.35M 35s 117800K .......... .......... .......... .......... .......... 22% 52.4M 35s 117850K .......... .......... .......... .......... .......... 22% 56.1M 35s 117900K .......... .......... .......... .......... .......... 22% 88.1M 35s 117950K .......... .......... .......... .......... .......... 22% 91.4M 35s 118000K .......... .......... .......... .......... .......... 22% 69.5M 35s 118050K .......... .......... .......... .......... .......... 22% 24.3M 35s 118100K .......... .......... .......... .......... .......... 22% 52.1M 35s 118150K .......... .......... .......... .......... .......... 22% 64.2M 35s 118200K .......... .......... .......... .......... .......... 22% 25.0M 35s 118250K .......... .......... .......... .......... .......... 22% 97.7M 35s 118300K .......... .......... .......... .......... .......... 22% 109M 35s 118350K .......... .......... .......... .......... .......... 22% 38.9M 35s 118400K .......... .......... .......... .......... .......... 22% 186M 35s 118450K .......... .......... .......... .......... .......... 22% 62.0M 35s 118500K .......... .......... .......... .......... .......... 22% 22.0M 35s 118550K .......... .......... .......... .......... .......... 22% 108M 35s 118600K .......... .......... .......... .......... .......... 22% 137M 35s 118650K .......... .......... .......... .......... .......... 22% 76.1M 35s 118700K .......... .......... .......... .......... .......... 22% 72.8M 35s 118750K .......... .......... .......... .......... .......... 22% 9.63M 35s 118800K .......... .......... .......... .......... .......... 22% 74.5M 35s 118850K .......... .......... .......... .......... .......... 22% 55.7M 35s 118900K .......... .......... .......... .......... .......... 22% 182M 35s 118950K .......... .......... .......... .......... .......... 22% 93.7M 35s 119000K .......... .......... .......... .......... .......... 22% 113M 35s 119050K .......... .......... .......... .......... .......... 22% 4.47M 35s 119100K .......... .......... .......... .......... .......... 22% 54.2M 35s 119150K .......... .......... .......... .......... .......... 22% 66.5M 35s 119200K .......... .......... .......... .......... .......... 22% 17.8M 35s 119250K .......... .......... .......... .......... .......... 22% 68.2M 35s 119300K .......... .......... .......... .......... .......... 22% 144M 35s 119350K .......... .......... .......... .......... .......... 22% 7.14M 35s 119400K .......... .......... .......... .......... 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.......... 23% 20.6M 34s 127900K .......... .......... .......... .......... .......... 23% 108M 34s 127950K .......... .......... .......... .......... .......... 24% 84.2M 34s 128000K .......... .......... .......... .......... .......... 24% 6.01M 34s 128050K .......... .......... .......... .......... .......... 24% 59.8M 34s 128100K .......... .......... .......... .......... .......... 24% 79.4M 34s 128150K .......... .......... .......... .......... .......... 24% 107M 34s 128200K .......... .......... .......... .......... .......... 24% 81.5M 34s 128250K .......... .......... .......... .......... .......... 24% 89.9M 34s 128300K .......... .......... .......... .......... .......... 24% 80.3M 34s 128350K .......... .......... .......... .......... .......... 24% 69.1M 34s 128400K .......... .......... .......... .......... .......... 24% 14.3M 34s 128450K .......... .......... .......... .......... .......... 24% 47.5M 34s 128500K .......... .......... .......... .......... .......... 24% 67.9M 34s 128550K .......... .......... .......... .......... .......... 24% 131M 34s 128600K .......... .......... .......... .......... .......... 24% 81.9M 34s 128650K .......... .......... .......... .......... .......... 24% 80.2M 34s 128700K .......... .......... .......... .......... .......... 24% 89.9M 34s 128750K .......... .......... .......... .......... .......... 24% 4.51M 34s 128800K .......... .......... .......... .......... .......... 24% 99.9M 34s 128850K .......... .......... .......... .......... .......... 24% 24.2M 33s 128900K .......... .......... .......... .......... .......... 24% 81.2M 33s 128950K .......... .......... .......... .......... .......... 24% 71.0M 33s 129000K .......... .......... .......... .......... .......... 24% 8.49M 33s 129050K .......... .......... .......... .......... .......... 24% 48.1M 33s 129100K .......... .......... .......... .......... .......... 24% 100M 33s 129150K .......... .......... .......... .......... .......... 24% 139M 33s 129200K .......... .......... .......... .......... .......... 24% 106M 33s 129250K .......... .......... .......... .......... .......... 24% 79.9M 33s 129300K .......... .......... .......... .......... .......... 24% 146M 33s 129350K .......... .......... .......... .......... .......... 24% 7.52M 33s 129400K .......... .......... .......... .......... .......... 24% 81.0M 33s 129450K .......... .......... .......... .......... .......... 24% 22.7M 33s 129500K .......... .......... .......... .......... .......... 24% 166M 33s 129550K .......... .......... .......... .......... .......... 24% 171M 33s 129600K .......... .......... .......... .......... .......... 24% 15.4M 33s 129650K .......... .......... .......... .......... .......... 24% 13.1M 33s 129700K .......... .......... .......... .......... .......... 24% 62.3M 33s 129750K .......... .......... .......... .......... .......... 24% 143M 33s 129800K .......... .......... .......... .......... .......... 24% 111M 33s 129850K .......... .......... .......... .......... .......... 24% 88.1M 33s 129900K .......... .......... .......... .......... .......... 24% 152M 33s 129950K .......... .......... .......... .......... .......... 24% 5.76M 33s 130000K .......... .......... .......... .......... .......... 24% 69.9M 33s 130050K .......... .......... .......... .......... .......... 24% 4.63M 33s 130100K .......... .......... .......... .......... .......... 24% 90.6M 33s 130150K .......... .......... .......... .......... .......... 24% 82.9M 33s 130200K .......... .......... .......... .......... .......... 24% 108M 33s 130250K .......... .......... .......... .......... .......... 24% 98.4M 33s 130300K .......... .......... .......... .......... .......... 24% 205M 33s 130350K .......... .......... .......... .......... .......... 24% 206M 33s 130400K .......... .......... .......... .......... .......... 24% 228M 33s 130450K .......... .......... .......... .......... .......... 24% 171M 33s 130500K .......... .......... .......... .......... .......... 24% 121M 33s 130550K .......... .......... .......... .......... .......... 24% 10.1M 33s 130600K .......... .......... .......... .......... .......... 24% 71.8M 33s 130650K .......... .......... .......... .......... .......... 24% 183M 33s 130700K .......... .......... .......... .......... .......... 24% 101M 33s 130750K .......... .......... .......... .......... .......... 24% 12.6M 33s 130800K .......... .......... .......... .......... .......... 24% 134M 33s 130850K .......... .......... .......... .......... .......... 24% 91.4M 33s 130900K .......... .......... .......... .......... .......... 24% 184M 33s 130950K .......... .......... .......... .......... .......... 24% 6.46M 33s 131000K .......... .......... .......... .......... .......... 24% 112M 33s 131050K .......... .......... .......... .......... .......... 24% 88.0M 33s 131100K .......... .......... .......... .......... .......... 24% 72.0M 33s 131150K .......... .......... .......... .......... .......... 24% 19.4M 33s 131200K .......... .......... .......... .......... .......... 24% 169M 33s 131250K .......... .......... .......... .......... .......... 24% 152M 33s 131300K .......... .......... .......... .......... .......... 24% 5.70M 33s 131350K .......... .......... .......... .......... .......... 24% 181M 33s 131400K .......... .......... .......... .......... .......... 24% 144M 33s 131450K .......... .......... .......... .......... .......... 24% 109M 33s 131500K .......... .......... .......... .......... .......... 24% 4.39M 33s 131550K .......... .......... .......... .......... .......... 24% 43.1M 33s 131600K .......... .......... .......... .......... .......... 24% 60.3M 33s 131650K .......... .......... .......... .......... .......... 24% 128M 33s 131700K .......... .......... .......... .......... .......... 24% 178M 33s 131750K .......... .......... .......... .......... .......... 24% 133M 33s 131800K .......... .......... .......... .......... .......... 24% 148M 33s 131850K .......... .......... .......... .......... .......... 24% 156M 33s 131900K .......... .......... .......... .......... .......... 24% 7.73M 33s 131950K .......... .......... .......... .......... .......... 24% 66.6M 33s 132000K .......... .......... .......... .......... .......... 24% 13.5M 33s 132050K .......... .......... .......... .......... .......... 24% 5.81M 33s 132100K .......... .......... .......... .......... .......... 24% 88.8M 33s 132150K .......... .......... .......... .......... .......... 24% 143M 33s 132200K .......... .......... .......... .......... .......... 24% 162M 33s 132250K .......... .......... .......... .......... .......... 24% 19.6M 33s 132300K .......... .......... .......... .......... .......... 24% 197M 33s 132350K .......... .......... .......... .......... .......... 24% 124M 33s 132400K .......... .......... .......... .......... .......... 24% 198M 33s 132450K .......... .......... .......... .......... .......... 24% 220M 33s 132500K .......... .......... .......... .......... .......... 24% 120M 33s 132550K .......... .......... .......... .......... .......... 24% 4.98M 33s 132600K .......... .......... .......... .......... .......... 24% 147M 33s 132650K .......... .......... .......... .......... .......... 24% 186M 33s 132700K .......... .......... .......... .......... .......... 24% 41.0M 33s 132750K .......... .......... .......... .......... .......... 24% 71.4M 33s 132800K .......... .......... .......... .......... .......... 24% 146M 33s 132850K .......... .......... .......... .......... .......... 24% 8.24M 33s 132900K .......... .......... .......... .......... .......... 24% 82.3M 33s 132950K .......... .......... .......... .......... .......... 24% 163M 33s 133000K .......... .......... .......... .......... .......... 24% 143M 33s 133050K .......... .......... .......... .......... .......... 24% 133M 33s 133100K .......... .......... .......... .......... .......... 24% 115M 33s 133150K .......... .......... .......... .......... .......... 24% 5.92M 33s 133200K .......... .......... .......... .......... .......... 24% 73.6M 33s 133250K .......... .......... .......... .......... .......... 25% 150M 33s 133300K .......... .......... .......... .......... .......... 25% 146M 32s 133350K .......... .......... .......... .......... .......... 25% 184M 32s 133400K .......... .......... .......... .......... .......... 25% 141M 32s 133450K .......... .......... .......... .......... .......... 25% 5.40M 32s 133500K .......... .......... .......... .......... .......... 25% 109M 32s 133550K .......... .......... .......... .......... .......... 25% 187M 32s 133600K .......... .......... .......... .......... .......... 25% 130M 32s 133650K .......... .......... .......... .......... .......... 25% 176M 32s 133700K .......... .......... .......... .......... .......... 25% 173M 32s 133750K .......... .......... .......... .......... .......... 25% 5.42M 32s 133800K .......... .......... .......... .......... .......... 25% 137M 32s 133850K .......... .......... .......... .......... .......... 25% 137M 32s 133900K .......... .......... .......... .......... .......... 25% 77.5M 32s 133950K .......... .......... .......... .......... .......... 25% 107M 32s 134000K .......... .......... .......... .......... .......... 25% 108M 32s 134050K .......... .......... .......... .......... .......... 25% 154M 32s 134100K .......... .......... .......... .......... .......... 25% 2.54M 32s 134150K .......... .......... .......... .......... .......... 25% 125M 32s 134200K .......... .......... .......... .......... .......... 25% 65.3M 32s 134250K .......... .......... .......... .......... .......... 25% 126M 32s 134300K .......... .......... .......... .......... .......... 25% 133M 32s 134350K .......... .......... .......... .......... .......... 25% 28.6M 32s 134400K .......... .......... .......... .......... .......... 25% 148M 32s 134450K .......... .......... .......... .......... .......... 25% 241M 32s 134500K .......... .......... .......... .......... .......... 25% 229M 32s 134550K .......... .......... .......... .......... .......... 25% 217M 32s 134600K .......... .......... .......... .......... .......... 25% 196M 32s 134650K .......... .......... .......... .......... .......... 25% 277M 32s 134700K .......... .......... .......... .......... .......... 25% 8.42M 32s 134750K .......... .......... .......... .......... .......... 25% 145M 32s 134800K .......... .......... .......... .......... .......... 25% 126M 32s 134850K .......... .......... .......... .......... .......... 25% 30.7M 32s 134900K .......... .......... .......... .......... .......... 25% 199M 32s 134950K .......... .......... .......... .......... .......... 25% 201M 32s 135000K .......... .......... .......... .......... .......... 25% 194M 32s 135050K .......... .......... .......... .......... .......... 25% 5.99M 32s 135100K .......... .......... .......... .......... .......... 25% 71.2M 32s 135150K .......... .......... .......... .......... .......... 25% 3.44M 32s 135200K .......... .......... .......... .......... .......... 25% 104M 32s 135250K .......... .......... .......... .......... .......... 25% 121M 32s 135300K .......... .......... .......... .......... .......... 25% 135M 32s 135350K .......... .......... .......... .......... .......... 25% 99.9M 32s 135400K .......... .......... .......... .......... .......... 25% 144M 32s 135450K .......... .......... .......... .......... .......... 25% 170M 32s 135500K .......... .......... .......... .......... .......... 25% 234M 32s 135550K .......... .......... .......... .......... .......... 25% 257M 32s 135600K .......... .......... .......... .......... .......... 25% 226M 32s 135650K .......... .......... .......... .......... .......... 25% 242M 32s 135700K .......... .......... .......... .......... .......... 25% 6.95M 32s 135750K .......... .......... .......... .......... .......... 25% 102M 32s 135800K .......... .......... .......... .......... .......... 25% 105M 32s 135850K .......... .......... .......... .......... .......... 25% 133M 32s 135900K .......... .......... .......... .......... .......... 25% 179M 32s 135950K .......... .......... .......... .......... .......... 25% 3.60M 32s 136000K .......... .......... .......... .......... .......... 25% 64.5M 32s 136050K .......... .......... .......... .......... .......... 25% 151M 32s 136100K .......... .......... .......... .......... .......... 25% 174M 32s 136150K .......... .......... .......... .......... .......... 25% 150M 32s 136200K .......... .......... .......... .......... .......... 25% 174M 32s 136250K .......... .......... .......... .......... .......... 25% 192M 32s 136300K .......... .......... .......... .......... .......... 25% 6.81M 32s 136350K .......... .......... .......... .......... .......... 25% 112M 32s 136400K .......... .......... .......... .......... .......... 25% 210M 32s 136450K .......... .......... .......... .......... .......... 25% 142M 32s 136500K .......... .......... .......... .......... .......... 25% 128M 32s 136550K .......... .......... .......... .......... .......... 25% 4.82M 32s 136600K .......... .......... .......... .......... .......... 25% 72.0M 32s 136650K .......... .......... .......... .......... .......... 25% 130M 32s 136700K .......... .......... .......... .......... .......... 25% 139M 32s 136750K .......... .......... .......... .......... .......... 25% 152M 32s 136800K .......... .......... .......... .......... .......... 25% 176M 32s 136850K .......... .......... .......... .......... .......... 25% 173M 32s 136900K .......... .......... .......... .......... .......... 25% 173M 32s 136950K .......... .......... .......... .......... .......... 25% 6.30M 32s 137000K .......... .......... .......... .......... .......... 25% 73.4M 32s 137050K .......... .......... .......... .......... .......... 25% 108M 32s 137100K .......... .......... .......... .......... .......... 25% 174M 32s 137150K .......... .......... .......... .......... .......... 25% 173M 32s 137200K .......... .......... .......... .......... .......... 25% 4.51M 32s 137250K .......... .......... .......... .......... .......... 25% 7.37M 32s 137300K .......... .......... .......... .......... .......... 25% 78.8M 32s 137350K .......... .......... .......... .......... .......... 25% 171M 32s 137400K .......... .......... .......... .......... .......... 25% 222M 32s 137450K .......... .......... .......... .......... .......... 25% 174M 32s 137500K .......... .......... .......... .......... .......... 25% 174M 32s 137550K .......... .......... .......... .......... .......... 25% 3.07M 32s 137600K .......... .......... .......... .......... .......... 25% 173M 32s 137650K .......... .......... .......... .......... .......... 25% 215M 32s 137700K .......... .......... .......... .......... .......... 25% 105M 32s 137750K .......... .......... .......... .......... .......... 25% 82.2M 32s 137800K .......... .......... .......... .......... .......... 25% 88.9M 32s 137850K .......... .......... .......... .......... .......... 25% 6.41M 32s 137900K .......... .......... .......... .......... .......... 25% 75.6M 32s 137950K .......... .......... .......... .......... .......... 25% 87.2M 32s 138000K .......... .......... .......... .......... .......... 25% 110M 32s 138050K .......... .......... .......... .......... .......... 25% 77.8M 32s 138100K .......... .......... .......... .......... .......... 25% 61.9M 32s 138150K .......... .......... .......... .......... .......... 25% 101M 31s 138200K .......... .......... .......... .......... .......... 25% 587K 32s 138250K .......... .......... .......... .......... .......... 25% 51.0M 32s 138300K .......... .......... .......... .......... .......... 25% 34.7M 32s 138350K .......... .......... .......... .......... .......... 25% 124M 32s 138400K .......... .......... .......... .......... .......... 25% 81.4M 32s 138450K .......... .......... .......... .......... .......... 25% 42.2M 32s 138500K .......... .......... .......... .......... .......... 25% 34.0M 32s 138550K .......... .......... .......... .......... .......... 25% 38.5M 32s 138600K .......... .......... .......... .......... .......... 26% 45.8M 32s 138650K .......... .......... .......... .......... .......... 26% 68.7M 32s 138700K .......... .......... .......... .......... .......... 26% 64.4M 32s 138750K .......... .......... .......... .......... .......... 26% 134M 32s 138800K .......... .......... .......... .......... .......... 26% 124M 32s 138850K .......... .......... .......... .......... .......... 26% 139M 32s 138900K .......... .......... .......... .......... .......... 26% 159M 32s 138950K .......... .......... .......... .......... .......... 26% 146M 32s 139000K .......... .......... .......... .......... .......... 26% 124M 32s 139050K .......... .......... .......... .......... .......... 26% 150M 31s 139100K .......... .......... .......... .......... .......... 26% 144M 31s 139150K .......... .......... .......... .......... .......... 26% 143M 31s 139200K .......... .......... .......... .......... .......... 26% 9.35M 31s 139250K .......... .......... .......... .......... .......... 26% 22.6M 31s 139300K .......... .......... .......... .......... .......... 26% 57.7M 31s 139350K .......... .......... .......... .......... .......... 26% 102M 31s 139400K .......... .......... .......... .......... .......... 26% 236M 31s 139450K .......... .......... .......... .......... .......... 26% 4.80M 31s 139500K .......... .......... .......... .......... .......... 26% 15.8M 31s 139550K .......... .......... .......... .......... 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26% 171M 31s 140250K .......... .......... .......... .......... .......... 26% 1.64M 31s 140300K .......... .......... .......... .......... .......... 26% 68.0M 31s 140350K .......... .......... .......... .......... .......... 26% 48.5M 31s 140400K .......... .......... .......... .......... .......... 26% 149M 31s 140450K .......... .......... .......... .......... .......... 26% 65.2M 31s 140500K .......... .......... .......... .......... .......... 26% 132M 31s 140550K .......... .......... .......... .......... .......... 26% 46.5M 31s 140600K .......... .......... .......... .......... .......... 26% 140M 31s 140650K .......... .......... .......... .......... .......... 26% 161M 31s 140700K .......... .......... .......... .......... .......... 26% 162M 31s 140750K .......... .......... .......... .......... .......... 26% 3.94M 31s 140800K .......... .......... .......... .......... .......... 26% 23.6M 31s 140850K .......... .......... .......... .......... .......... 26% 161M 31s 140900K .......... .......... .......... .......... .......... 26% 131M 31s 140950K .......... .......... .......... .......... .......... 26% 17.7M 31s 141000K .......... .......... .......... .......... .......... 26% 6.85M 31s 141050K .......... .......... .......... .......... .......... 26% 167M 31s 141100K .......... .......... .......... .......... .......... 26% 5.19M 31s 141150K .......... .......... .......... .......... .......... 26% 147M 31s 141200K .......... .......... .......... .......... .......... 26% 174M 31s 141250K .......... .......... .......... .......... .......... 26% 180M 31s 141300K .......... .......... .......... .......... .......... 26% 68.1M 31s 141350K .......... .......... .......... .......... .......... 26% 118M 31s 141400K .......... .......... .......... .......... .......... 26% 23.8M 31s 141450K .......... .......... .......... .......... .......... 26% 83.9M 31s 141500K .......... .......... .......... .......... .......... 26% 62.8M 31s 141550K .......... .......... .......... .......... .......... 26% 169M 31s 141600K .......... .......... .......... .......... .......... 26% 164M 31s 141650K .......... .......... .......... .......... .......... 26% 144M 31s 141700K .......... .......... .......... .......... .......... 26% 91.8M 31s 141750K .......... .......... .......... .......... .......... 26% 126M 31s 141800K .......... .......... .......... .......... .......... 26% 5.05M 31s 141850K .......... .......... .......... .......... .......... 26% 5.48M 31s 141900K .......... .......... .......... .......... .......... 26% 11.7M 31s 141950K .......... .......... .......... .......... .......... 26% 53.4M 31s 142000K .......... .......... .......... .......... .......... 26% 82.6M 31s 142050K .......... .......... .......... .......... .......... 26% 169M 31s 142100K .......... .......... .......... .......... .......... 26% 50.4M 31s 142150K .......... .......... .......... .......... .......... 26% 4.21M 31s 142200K .......... .......... .......... .......... .......... 26% 10.2M 31s 142250K .......... .......... .......... .......... .......... 26% 2.71M 31s 142300K .......... .......... .......... .......... .......... 26% 34.1M 31s 142350K .......... .......... .......... .......... .......... 26% 27.2M 31s 142400K .......... .......... .......... .......... .......... 26% 51.3M 31s 142450K .......... .......... .......... .......... .......... 26% 54.0M 31s 142500K .......... .......... .......... .......... .......... 26% 19.6M 31s 142550K .......... .......... .......... .......... .......... 26% 22.4M 31s 142600K .......... .......... .......... .......... .......... 26% 43.2M 31s 142650K .......... .......... .......... .......... .......... 26% 4.40M 31s 142700K .......... .......... .......... .......... .......... 26% 13.8M 31s 142750K .......... .......... .......... .......... .......... 26% 44.7M 31s 142800K .......... .......... .......... .......... .......... 26% 53.1M 31s 142850K .......... .......... .......... .......... .......... 26% 115M 31s 142900K .......... .......... .......... .......... .......... 26% 68.4M 31s 142950K .......... .......... .......... .......... .......... 26% 73.9M 31s 143000K .......... .......... .......... .......... .......... 26% 34.5M 31s 143050K .......... .......... .......... .......... .......... 26% 2.89M 31s 143100K .......... .......... .......... .......... .......... 26% 39.7M 31s 143150K .......... .......... .......... .......... .......... 26% 19.3M 31s 143200K .......... .......... .......... .......... .......... 26% 4.98M 31s 143250K .......... .......... .......... .......... .......... 26% 25.1M 31s 143300K .......... .......... .......... .......... .......... 26% 55.7M 31s 143350K .......... .......... .......... .......... .......... 26% 15.7M 31s 143400K .......... .......... .......... .......... .......... 26% 15.5M 31s 143450K .......... .......... .......... .......... .......... 26% 5.00M 31s 143500K .......... .......... .......... .......... .......... 26% 10.8M 31s 143550K .......... .......... .......... .......... .......... 26% 81.7M 31s 143600K .......... .......... .......... .......... .......... 26% 140M 31s 143650K .......... .......... .......... .......... .......... 26% 121M 31s 143700K .......... .......... .......... .......... .......... 26% 18.2M 31s 143750K .......... .......... .......... .......... .......... 26% 22.7M 31s 143800K .......... .......... .......... .......... .......... 26% 59.7M 31s 143850K .......... .......... .......... .......... .......... 26% 65.8M 31s 143900K .......... .......... .......... .......... .......... 26% 92.1M 31s 143950K .......... .......... .......... .......... .......... 27% 36.1M 31s 144000K .......... .......... .......... .......... .......... 27% 21.7M 31s 144050K .......... .......... .......... .......... .......... 27% 130M 31s 144100K .......... .......... .......... .......... .......... 27% 151M 31s 144150K .......... .......... .......... .......... .......... 27% 174M 31s 144200K .......... .......... .......... .......... .......... 27% 38.9M 31s 144250K .......... .......... .......... .......... .......... 27% 171M 31s 144300K .......... .......... .......... .......... .......... 27% 160M 31s 144350K .......... .......... .......... .......... .......... 27% 139M 31s 144400K .......... .......... .......... .......... .......... 27% 29.3M 31s 144450K .......... .......... .......... .......... .......... 27% 133M 31s 144500K .......... .......... .......... .......... .......... 27% 159M 31s 144550K .......... .......... .......... .......... .......... 27% 125M 31s 144600K .......... .......... .......... .......... .......... 27% 148M 31s 144650K .......... .......... .......... .......... .......... 27% 39.5M 31s 144700K .......... .......... .......... .......... .......... 27% 154M 31s 144750K .......... .......... .......... .......... .......... 27% 28.6M 31s 144800K 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.......... .......... .......... 34% 115M 25s 185200K .......... .......... .......... .......... .......... 34% 116M 25s 185250K .......... .......... .......... .......... .......... 34% 4.70M 25s 185300K .......... .......... .......... .......... .......... 34% 114M 25s 185350K .......... .......... .......... .......... .......... 34% 6.59M 25s 185400K .......... .......... .......... .......... .......... 34% 123M 25s 185450K .......... .......... .......... .......... .......... 34% 126M 25s 185500K .......... .......... .......... .......... .......... 34% 187M 25s 185550K .......... .......... .......... .......... .......... 34% 190M 25s 185600K .......... .......... .......... .......... .......... 34% 141M 25s 185650K .......... .......... .......... .......... .......... 34% 203M 25s 185700K .......... .......... .......... .......... .......... 34% 95.7M 25s 185750K .......... .......... .......... .......... .......... 34% 261M 25s 185800K .......... .......... 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.......... .......... .......... 34% 23.3M 25s 186500K .......... .......... .......... .......... .......... 34% 25.3M 25s 186550K .......... .......... .......... .......... .......... 34% 135M 25s 186600K .......... .......... .......... .......... .......... 35% 132M 25s 186650K .......... .......... .......... .......... .......... 35% 123M 25s 186700K .......... .......... .......... .......... .......... 35% 14.6M 25s 186750K .......... .......... .......... .......... .......... 35% 109M 25s 186800K .......... .......... .......... .......... .......... 35% 102M 25s 186850K .......... .......... .......... .......... .......... 35% 22.9M 25s 186900K .......... .......... .......... .......... .......... 35% 149M 25s 186950K .......... .......... .......... .......... .......... 35% 7.02M 25s 187000K .......... .......... .......... .......... .......... 35% 86.9M 25s 187050K .......... .......... .......... .......... .......... 35% 91.4M 25s 187100K .......... .......... .......... .......... .......... 35% 125M 25s 187150K .......... .......... .......... .......... .......... 35% 215M 25s 187200K .......... .......... .......... .......... .......... 35% 47.5M 25s 187250K .......... .......... .......... .......... .......... 35% 9.76M 25s 187300K .......... .......... .......... .......... .......... 35% 70.7M 25s 187350K .......... .......... .......... .......... .......... 35% 493K 25s 187400K .......... .......... .......... .......... .......... 35% 74.8M 25s 187450K .......... .......... .......... .......... .......... 35% 112M 25s 187500K .......... .......... .......... .......... .......... 35% 72.6M 25s 187550K .......... .......... .......... .......... .......... 35% 58.3M 25s 187600K .......... .......... .......... .......... .......... 35% 74.1M 25s 187650K .......... .......... .......... .......... .......... 35% 184M 25s 187700K .......... .......... .......... .......... .......... 35% 160M 25s 187750K .......... .......... .......... .......... .......... 35% 65.7M 25s 187800K .......... .......... .......... .......... .......... 35% 5.44M 25s 187850K .......... .......... .......... .......... .......... 35% 134M 25s 187900K .......... .......... .......... .......... .......... 35% 149M 25s 187950K .......... .......... .......... .......... .......... 35% 152M 25s 188000K .......... .......... .......... .......... .......... 35% 167M 25s 188050K .......... .......... .......... .......... .......... 35% 184M 25s 188100K .......... .......... .......... .......... .......... 35% 40.6M 25s 188150K .......... .......... .......... .......... .......... 35% 142M 25s 188200K .......... .......... .......... .......... .......... 35% 198M 25s 188250K .......... .......... .......... .......... .......... 35% 195M 25s 188300K .......... .......... .......... .......... .......... 35% 208M 25s 188350K .......... .......... .......... .......... .......... 35% 163M 25s 188400K .......... .......... .......... .......... .......... 35% 134M 25s 188450K .......... .......... .......... .......... .......... 35% 164M 25s 188500K .......... .......... .......... .......... .......... 35% 140M 25s 188550K .......... .......... .......... .......... .......... 35% 202M 25s 188600K .......... .......... .......... .......... .......... 35% 155M 25s 188650K .......... .......... .......... .......... .......... 35% 204M 25s 188700K .......... .......... .......... .......... .......... 35% 169M 25s 188750K .......... .......... .......... .......... .......... 35% 204M 25s 188800K .......... .......... .......... .......... .......... 35% 203M 25s 188850K .......... .......... .......... .......... .......... 35% 182M 25s 188900K .......... .......... .......... .......... .......... 35% 203M 25s 188950K .......... .......... .......... .......... .......... 35% 20.4M 25s 189000K .......... .......... .......... .......... .......... 35% 206M 25s 189050K .......... .......... .......... .......... .......... 35% 227M 25s 189100K .......... .......... .......... .......... .......... 35% 168M 25s 189150K .......... .......... .......... .......... .......... 35% 191M 25s 189200K .......... .......... .......... .......... .......... 35% 6.48M 25s 189250K .......... .......... .......... .......... .......... 35% 61.7M 25s 189300K .......... .......... .......... .......... .......... 35% 167M 25s 189350K .......... .......... .......... .......... .......... 35% 169M 25s 189400K .......... .......... .......... .......... .......... 35% 8.16M 25s 189450K .......... .......... .......... .......... .......... 35% 155M 25s 189500K .......... .......... .......... .......... .......... 35% 177M 25s 189550K .......... .......... .......... .......... .......... 35% 125M 25s 189600K .......... .......... .......... .......... .......... 35% 106M 25s 189650K .......... .......... .......... .......... .......... 35% 168M 25s 189700K .......... .......... .......... .......... .......... 35% 97.5M 25s 189750K .......... .......... .......... .......... .......... 35% 157M 25s 189800K .......... .......... .......... .......... .......... 35% 4.38M 25s 189850K .......... .......... .......... .......... .......... 35% 134M 25s 189900K .......... .......... .......... .......... .......... 35% 145M 25s 189950K .......... .......... .......... .......... .......... 35% 22.9M 25s 190000K .......... .......... .......... .......... .......... 35% 59.2M 25s 190050K .......... .......... .......... .......... .......... 35% 126M 25s 190100K .......... .......... .......... .......... .......... 35% 8.01M 25s 190150K .......... .......... .......... .......... .......... 35% 83.5M 24s 190200K .......... .......... .......... .......... .......... 35% 135M 24s 190250K .......... .......... .......... .......... .......... 35% 176M 24s 190300K .......... .......... .......... .......... .......... 35% 210M 24s 190350K .......... .......... .......... .......... .......... 35% 4.53M 24s 190400K .......... .......... .......... .......... .......... 35% 156M 24s 190450K .......... .......... .......... .......... .......... 35% 458K 25s 190500K .......... .......... .......... .......... .......... 35% 118M 25s 190550K .......... .......... .......... .......... .......... 35% 174M 25s 190600K .......... .......... .......... .......... .......... 35% 141M 25s 190650K .......... .......... .......... .......... .......... 35% 190M 25s 190700K .......... .......... .......... .......... .......... 35% 159M 25s 190750K .......... .......... .......... .......... .......... 35% 79.3M 25s 190800K .......... .......... .......... .......... .......... 35% 94.4M 25s 190850K .......... .......... .......... .......... .......... 35% 155M 25s 190900K .......... .......... .......... .......... .......... 35% 61.3M 25s 190950K .......... .......... .......... .......... .......... 35% 124M 25s 191000K .......... .......... .......... .......... .......... 35% 49.8M 25s 191050K .......... .......... .......... .......... .......... 35% 117M 25s 191100K .......... .......... .......... .......... .......... 35% 99.6M 25s 191150K .......... .......... .......... .......... .......... 35% 204M 25s 191200K .......... .......... .......... .......... .......... 35% 81.0M 25s 191250K .......... .......... .......... .......... .......... 35% 110M 25s 191300K .......... .......... .......... .......... .......... 35% 202M 24s 191350K .......... .......... .......... .......... .......... 35% 133M 24s 191400K .......... .......... .......... .......... .......... 35% 212M 24s 191450K .......... .......... .......... .......... .......... 35% 241K 25s 191500K .......... .......... .......... .......... .......... 35% 173M 25s 191550K .......... .......... .......... .......... .......... 35% 195M 25s 191600K .......... .......... .......... .......... .......... 35% 162M 25s 191650K .......... .......... .......... .......... .......... 35% 126M 25s 191700K .......... .......... .......... .......... .......... 35% 108M 25s 191750K .......... .......... .......... .......... .......... 35% 157M 25s 191800K .......... .......... .......... .......... .......... 35% 124M 25s 191850K .......... .......... .......... .......... .......... 35% 37.9M 25s 191900K .......... .......... .......... .......... .......... 36% 159M 25s 191950K .......... .......... .......... .......... .......... 36% 171M 25s 192000K .......... .......... .......... .......... .......... 36% 207M 25s 192050K .......... .......... .......... .......... .......... 36% 110M 25s 192100K .......... .......... .......... .......... .......... 36% 114M 25s 192150K .......... .......... .......... .......... .......... 36% 133M 25s 192200K .......... .......... .......... .......... .......... 36% 127M 25s 192250K .......... .......... .......... .......... .......... 36% 195M 25s 192300K .......... .......... .......... .......... .......... 36% 209M 25s 192350K .......... .......... .......... .......... .......... 36% 154M 25s 192400K .......... .......... .......... .......... .......... 36% 148M 25s 192450K .......... .......... .......... .......... .......... 36% 151M 25s 192500K .......... .......... .......... .......... .......... 36% 160M 25s 192550K .......... .......... .......... .......... .......... 36% 131M 25s 192600K .......... .......... .......... .......... .......... 36% 99.0M 25s 192650K .......... .......... .......... .......... .......... 36% 205M 25s 192700K .......... .......... .......... .......... .......... 36% 13.0M 25s 192750K .......... .......... .......... .......... .......... 36% 131M 25s 192800K .......... .......... .......... .......... .......... 36% 91.3M 25s 192850K .......... .......... .......... .......... .......... 36% 112M 25s 192900K .......... .......... .......... .......... .......... 36% 106M 25s 192950K .......... .......... .......... .......... .......... 36% 100M 25s 193000K .......... .......... .......... .......... .......... 36% 5.23M 25s 193050K .......... .......... .......... .......... .......... 36% 101M 25s 193100K .......... .......... .......... .......... .......... 36% 97.9M 25s 193150K .......... .......... .......... .......... .......... 36% 148M 25s 193200K .......... .......... .......... .......... .......... 36% 111M 25s 193250K .......... .......... .......... .......... .......... 36% 132M 25s 193300K .......... .......... .......... .......... .......... 36% 6.62M 25s 193350K .......... .......... .......... .......... .......... 36% 79.8M 25s 193400K .......... .......... .......... .......... .......... 36% 116M 25s 193450K .......... .......... .......... .......... .......... 36% 81.5M 25s 193500K .......... .......... .......... .......... .......... 36% 822K 25s 193550K .......... .......... .......... .......... .......... 36% 108M 25s 193600K .......... .......... .......... .......... .......... 36% 78.5M 25s 193650K .......... .......... .......... .......... .......... 36% 62.1M 25s 193700K .......... .......... .......... .......... .......... 36% 23.7M 25s 193750K .......... .......... .......... .......... .......... 36% 111M 25s 193800K .......... .......... .......... .......... .......... 36% 181M 25s 193850K .......... .......... .......... .......... .......... 36% 163M 25s 193900K .......... .......... .......... .......... .......... 36% 51.5M 25s 193950K .......... .......... .......... .......... .......... 36% 95.9M 25s 194000K .......... .......... .......... .......... .......... 36% 89.9M 25s 194050K .......... .......... .......... .......... .......... 36% 190M 25s 194100K .......... .......... .......... .......... .......... 36% 177M 24s 194150K .......... .......... .......... .......... .......... 36% 183M 24s 194200K .......... .......... .......... .......... .......... 36% 173M 24s 194250K .......... .......... .......... .......... .......... 36% 195M 24s 194300K .......... .......... .......... .......... .......... 36% 204M 24s 194350K .......... .......... .......... .......... .......... 36% 185M 24s 194400K .......... .......... .......... .......... .......... 36% 210M 24s 194450K .......... .......... .......... .......... .......... 36% 167M 24s 194500K .......... .......... .......... .......... .......... 36% 203M 24s 194550K .......... .......... .......... .......... .......... 36% 158M 24s 194600K .......... .......... .......... .......... .......... 36% 180M 24s 194650K .......... .......... .......... .......... .......... 36% 173M 24s 194700K .......... .......... .......... .......... .......... 36% 167M 24s 194750K .......... .......... .......... .......... .......... 36% 6.19M 24s 194800K .......... .......... .......... .......... .......... 36% 191M 24s 194850K .......... .......... .......... .......... .......... 36% 139M 24s 194900K .......... .......... .......... .......... .......... 36% 205M 24s 194950K .......... .......... .......... .......... .......... 36% 159M 24s 195000K .......... .......... .......... .......... .......... 36% 186M 24s 195050K .......... .......... .......... .......... .......... 36% 5.08M 24s 195100K .......... .......... .......... .......... .......... 36% 5.03M 24s 195150K .......... .......... .......... .......... .......... 36% 28.6M 24s 195200K .......... .......... .......... .......... .......... 36% 105M 24s 195250K .......... .......... .......... .......... .......... 36% 169M 24s 195300K .......... .......... .......... .......... .......... 36% 220M 24s 195350K .......... .......... .......... .......... .......... 36% 205M 24s 195400K .......... .......... .......... .......... .......... 36% 178M 24s 195450K .......... .......... .......... .......... .......... 36% 155M 24s 195500K .......... .......... .......... .......... .......... 36% 168M 24s 195550K .......... .......... .......... .......... .......... 36% 105M 24s 195600K .......... .......... .......... .......... .......... 36% 6.96M 24s 195650K .......... .......... .......... .......... .......... 36% 124M 24s 195700K .......... .......... .......... .......... .......... 36% 115M 24s 195750K .......... .......... .......... .......... .......... 36% 156M 24s 195800K .......... .......... .......... .......... .......... 36% 95.2M 24s 195850K .......... .......... .......... .......... .......... 36% 146M 24s 195900K .......... .......... .......... .......... .......... 36% 4.04M 24s 195950K .......... .......... .......... .......... .......... 36% 178M 24s 196000K .......... .......... .......... .......... .......... 36% 198M 24s 196050K .......... .......... .......... .......... .......... 36% 133M 24s 196100K .......... .......... .......... .......... .......... 36% 120M 24s 196150K .......... .......... .......... .......... .......... 36% 139M 24s 196200K .......... .......... .......... .......... .......... 36% 7.43M 24s 196250K .......... .......... .......... .......... .......... 36% 94.1M 24s 196300K .......... .......... .......... .......... .......... 36% 145M 24s 196350K .......... .......... .......... .......... .......... 36% 174M 24s 196400K .......... .......... .......... .......... .......... 36% 258M 24s 196450K .......... .......... .......... .......... .......... 36% 172M 24s 196500K .......... .......... .......... .......... .......... 36% 4.68M 24s 196550K .......... .......... .......... .......... .......... 36% 189M 24s 196600K .......... .......... .......... .......... .......... 36% 2.34M 24s 196650K .......... .......... .......... .......... .......... 36% 68.4M 24s 196700K .......... .......... .......... .......... .......... 36% 86.9M 24s 196750K .......... .......... .......... .......... .......... 36% 88.3M 24s 196800K .......... .......... .......... .......... .......... 36% 155M 24s 196850K .......... .......... .......... .......... .......... 36% 159M 24s 196900K .......... .......... .......... .......... .......... 36% 191M 24s 196950K .......... .......... .......... .......... .......... 36% 154M 24s 197000K .......... .......... .......... .......... .......... 36% 150M 24s 197050K .......... .......... .......... .......... .......... 36% 7.30M 24s 197100K .......... .......... .......... .......... .......... 36% 80.0M 24s 197150K .......... .......... .......... .......... .......... 36% 152M 24s 197200K .......... .......... .......... .......... .......... 36% 142M 24s 197250K .......... .......... .......... .......... .......... 37% 164M 24s 197300K .......... .......... .......... .......... .......... 37% 184M 24s 197350K .......... .......... .......... .......... .......... 37% 7.06M 24s 197400K .......... .......... .......... .......... .......... 37% 108M 24s 197450K .......... .......... .......... .......... .......... 37% 144M 24s 197500K .......... .......... .......... .......... .......... 37% 132M 24s 197550K .......... .......... .......... .......... .......... 37% 186M 24s 197600K .......... .......... .......... .......... .......... 37% 590K 24s 197650K .......... .......... .......... .......... .......... 37% 141M 24s 197700K .......... .......... .......... .......... .......... 37% 82.3M 24s 197750K .......... .......... .......... .......... .......... 37% 127M 24s 197800K .......... .......... .......... .......... .......... 37% 28.4M 24s 197850K .......... .......... .......... .......... .......... 37% 87.5M 24s 197900K .......... .......... .......... .......... .......... 37% 82.5M 24s 197950K .......... .......... .......... .......... .......... 37% 73.8M 24s 198000K .......... .......... .......... .......... .......... 37% 105M 24s 198050K .......... .......... .......... .......... .......... 37% 66.3M 24s 198100K .......... .......... .......... .......... .......... 37% 135M 24s 198150K .......... .......... .......... .......... .......... 37% 133M 24s 198200K .......... .......... .......... .......... .......... 37% 97.7M 24s 198250K .......... .......... .......... .......... .......... 37% 114M 24s 198300K .......... .......... .......... .......... .......... 37% 98.4M 24s 198350K .......... .......... .......... .......... .......... 37% 168M 24s 198400K .......... .......... .......... .......... .......... 37% 211M 24s 198450K .......... .......... .......... .......... .......... 37% 191M 24s 198500K .......... .......... .......... .......... .......... 37% 173M 24s 198550K .......... .......... .......... .......... .......... 37% 197M 24s 198600K .......... .......... .......... .......... .......... 37% 186M 24s 198650K .......... .......... .......... .......... .......... 37% 559K 24s 198700K .......... .......... .......... .......... .......... 37% 95.6M 24s 198750K .......... .......... .......... .......... .......... 37% 51.3M 24s 198800K .......... .......... .......... .......... .......... 37% 81.5M 24s 198850K .......... .......... .......... .......... .......... 37% 54.1M 24s 198900K .......... .......... .......... .......... .......... 37% 119M 24s 198950K .......... .......... .......... .......... .......... 37% 117M 24s 199000K .......... .......... .......... .......... .......... 37% 114M 24s 199050K .......... .......... .......... .......... .......... 37% 143M 24s 199100K .......... .......... .......... .......... .......... 37% 193M 24s 199150K .......... .......... .......... .......... .......... 37% 221M 24s 199200K .......... .......... .......... .......... .......... 37% 180M 24s 199250K .......... .......... .......... .......... .......... 37% 221M 24s 199300K .......... .......... .......... .......... .......... 37% 253M 24s 199350K .......... .......... .......... .......... .......... 37% 181M 24s 199400K .......... .......... .......... .......... .......... 37% 196M 24s 199450K .......... .......... .......... .......... .......... 37% 181M 24s 199500K .......... .......... .......... .......... .......... 37% 212M 24s 199550K .......... .......... .......... .......... .......... 37% 190M 24s 199600K .......... .......... .......... .......... .......... 37% 191M 24s 199650K .......... .......... .......... .......... .......... 37% 2.61M 24s 199700K .......... .......... .......... .......... .......... 37% 84.2M 24s 199750K .......... .......... .......... .......... .......... 37% 180M 24s 199800K .......... .......... .......... .......... .......... 37% 222M 24s 199850K .......... .......... .......... .......... .......... 37% 193M 24s 199900K .......... .......... .......... .......... .......... 37% 221M 24s 199950K .......... .......... .......... .......... .......... 37% 183M 24s 200000K .......... .......... .......... .......... .......... 37% 223M 24s 200050K .......... .......... .......... .......... .......... 37% 227M 24s 200100K .......... .......... .......... .......... .......... 37% 194M 24s 200150K .......... .......... .......... .......... .......... 37% 218M 24s 200200K .......... .......... .......... .......... .......... 37% 194M 24s 200250K .......... .......... .......... .......... .......... 37% 199M 24s 200300K .......... .......... .......... .......... .......... 37% 210M 24s 200350K .......... .......... .......... .......... .......... 37% 192M 24s 200400K .......... .......... .......... .......... .......... 37% 8.86M 24s 200450K .......... .......... .......... .......... .......... 37% 143M 24s 200500K .......... .......... .......... .......... .......... 37% 186M 24s 200550K .......... .......... .......... .......... .......... 37% 120M 24s 200600K .......... .......... .......... .......... .......... 37% 86.4M 24s 200650K .......... .......... .......... .......... .......... 37% 156M 24s 200700K .......... .......... .......... .......... .......... 37% 1.65M 24s 200750K .......... .......... .......... .......... .......... 37% 117M 24s 200800K .......... .......... 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.......... 37% 13.7M 24s 202150K .......... .......... .......... .......... .......... 37% 198M 24s 202200K .......... .......... .......... .......... .......... 37% 6.33M 24s 202250K .......... .......... .......... .......... .......... 37% 78.3M 24s 202300K .......... .......... .......... .......... .......... 37% 211M 24s 202350K .......... .......... .......... .......... .......... 37% 187M 24s 202400K .......... .......... .......... .......... .......... 37% 216M 24s 202450K .......... .......... .......... .......... .......... 37% 21.0M 24s 202500K .......... .......... .......... .......... .......... 37% 109M 24s 202550K .......... .......... .......... .......... .......... 37% 7.08M 24s 202600K .......... .......... .......... .......... .......... 38% 176M 24s 202650K .......... .......... .......... .......... .......... 38% 193M 24s 202700K .......... .......... .......... .......... .......... 38% 164M 24s 202750K .......... .......... .......... .......... 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22s 221700K .......... .......... .......... .......... .......... 41% 180M 22s 221750K .......... .......... .......... .......... .......... 41% 211M 22s 221800K .......... .......... .......... .......... .......... 41% 152M 22s 221850K .......... .......... .......... .......... .......... 41% 6.35M 22s 221900K .......... .......... .......... .......... .......... 41% 244M 22s 221950K .......... .......... .......... .......... .......... 41% 174M 22s 222000K .......... .......... .......... .......... .......... 41% 158M 22s 222050K .......... .......... .......... .......... .......... 41% 182M 22s 222100K .......... .......... .......... .......... .......... 41% 7.15M 22s 222150K .......... .......... .......... .......... .......... 41% 119M 22s 222200K .......... .......... .......... .......... .......... 41% 634K 22s 222250K .......... .......... .......... .......... .......... 41% 44.1M 22s 222300K .......... .......... .......... .......... .......... 41% 163M 22s 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43% 203M 21s 234100K .......... .......... .......... .......... .......... 43% 73.1M 21s 234150K .......... .......... .......... .......... .......... 43% 125M 21s 234200K .......... .......... .......... .......... .......... 43% 75.7M 21s 234250K .......... .......... .......... .......... .......... 43% 108M 21s 234300K .......... .......... .......... .......... .......... 43% 148M 21s 234350K .......... .......... .......... .......... .......... 43% 171M 21s 234400K .......... .......... .......... .......... .......... 43% 190M 21s 234450K .......... .......... .......... .......... .......... 43% 411K 21s 234500K .......... .......... .......... .......... .......... 43% 42.9M 21s 234550K .......... .......... .......... .......... .......... 44% 86.4M 21s 234600K .......... .......... .......... .......... .......... 44% 104M 21s 234650K .......... .......... .......... .......... .......... 44% 134M 21s 234700K .......... .......... .......... .......... .......... 44% 75.5M 21s 234750K .......... .......... .......... .......... .......... 44% 160M 21s 234800K .......... .......... .......... .......... .......... 44% 159M 21s 234850K .......... .......... .......... .......... .......... 44% 71.6M 21s 234900K .......... .......... .......... .......... .......... 44% 124M 21s 234950K .......... .......... .......... .......... .......... 44% 125M 21s 235000K .......... .......... .......... .......... .......... 44% 128M 21s 235050K .......... .......... .......... .......... .......... 44% 171M 21s 235100K .......... .......... .......... .......... .......... 44% 125M 21s 235150K .......... .......... .......... .......... .......... 44% 135M 21s 235200K .......... .......... .......... .......... .......... 44% 159M 21s 235250K .......... .......... .......... .......... .......... 44% 270M 21s 235300K .......... .......... .......... .......... .......... 44% 258M 21s 235350K .......... .......... .......... .......... .......... 44% 208M 21s 235400K .......... .......... .......... .......... .......... 44% 225M 21s 235450K .......... .......... .......... .......... .......... 44% 268M 21s 235500K .......... .......... .......... .......... .......... 44% 202M 21s 235550K .......... .......... .......... .......... .......... 44% 330M 21s 235600K .......... .......... .......... .......... .......... 44% 56.7M 21s 235650K .......... .......... .......... .......... .......... 44% 193M 21s 235700K .......... .......... .......... .......... .......... 44% 6.54M 21s 235750K .......... .......... .......... .......... .......... 44% 153M 21s 235800K .......... .......... .......... .......... .......... 44% 100M 21s 235850K .......... .......... .......... .......... .......... 44% 136M 21s 235900K .......... .......... .......... .......... .......... 44% 133M 21s 235950K .......... .......... .......... .......... .......... 44% 32.8M 21s 236000K .......... .......... .......... .......... .......... 44% 8.11M 21s 236050K 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.......... .......... .......... .......... 48% 129M 19s 260200K .......... .......... .......... .......... .......... 48% 168M 19s 260250K .......... .......... .......... .......... .......... 48% 179M 19s 260300K .......... .......... .......... .......... .......... 48% 194M 19s 260350K .......... .......... .......... .......... .......... 48% 161M 19s 260400K .......... .......... .......... .......... .......... 48% 137M 19s 260450K .......... .......... .......... .......... .......... 48% 136M 19s 260500K .......... .......... .......... .......... .......... 48% 156M 19s 260550K .......... .......... .......... .......... .......... 48% 174M 19s 260600K .......... .......... .......... .......... .......... 48% 76.5M 19s 260650K .......... .......... .......... .......... .......... 48% 174M 19s 260700K .......... .......... .......... .......... .......... 48% 191M 19s 260750K .......... .......... .......... .......... .......... 48% 187M 19s 260800K .......... .......... 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50% 323M 18s 267350K .......... .......... .......... .......... .......... 50% 213M 18s 267400K .......... .......... .......... .......... .......... 50% 265M 18s 267450K .......... .......... .......... .......... .......... 50% 14.2M 18s 267500K .......... .......... .......... .......... .......... 50% 26.0M 18s 267550K .......... .......... .......... .......... .......... 50% 188M 18s 267600K .......... .......... .......... .......... .......... 50% 159M 18s 267650K .......... .......... .......... .......... .......... 50% 28.7M 18s 267700K .......... .......... .......... .......... .......... 50% 166M 18s 267750K .......... .......... .......... .......... .......... 50% 10.5M 18s 267800K .......... .......... .......... .......... .......... 50% 132M 18s 267850K .......... .......... .......... .......... .......... 50% 24.7M 18s 267900K .......... .......... .......... .......... .......... 50% 159M 18s 267950K .......... .......... .......... .......... .......... 50% 144M 18s 268000K .......... .......... .......... .......... .......... 50% 146M 18s 268050K .......... .......... .......... .......... .......... 50% 9.17M 18s 268100K .......... .......... .......... .......... .......... 50% 76.3M 18s 268150K .......... .......... .......... .......... .......... 50% 211M 18s 268200K .......... .......... .......... .......... .......... 50% 184M 18s 268250K .......... .......... .......... .......... .......... 50% 2.69M 18s 268300K .......... .......... .......... .......... .......... 50% 127M 18s 268350K .......... .......... .......... .......... .......... 50% 170M 18s 268400K .......... .......... .......... .......... .......... 50% 148M 18s 268450K .......... .......... .......... .......... .......... 50% 136M 18s 268500K .......... .......... .......... .......... .......... 50% 168M 18s 268550K .......... .......... .......... .......... .......... 50% 155M 18s 268600K .......... .......... .......... .......... .......... 50% 203M 18s 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.......... .......... .......... 51% 86.0M 18s 274550K .......... .......... .......... .......... .......... 51% 27.7M 18s 274600K .......... .......... .......... .......... .......... 51% 168M 18s 274650K .......... .......... .......... .......... .......... 51% 106M 18s 274700K .......... .......... .......... .......... .......... 51% 133M 18s 274750K .......... .......... .......... .......... .......... 51% 138M 18s 274800K .......... .......... .......... .......... .......... 51% 9.29M 18s 274850K .......... .......... .......... .......... .......... 51% 26.8M 18s 274900K .......... .......... .......... .......... .......... 51% 101M 18s 274950K .......... .......... .......... .......... .......... 51% 164M 18s 275000K .......... .......... .......... .......... .......... 51% 196M 18s 275050K .......... .......... .......... .......... .......... 51% 28.4M 18s 275100K .......... .......... .......... .......... .......... 51% 7.37M 18s 275150K .......... .......... .......... .......... .......... 51% 96.3M 18s 275200K .......... .......... .......... .......... .......... 51% 123M 18s 275250K .......... .......... .......... .......... .......... 51% 171M 18s 275300K .......... .......... .......... .......... .......... 51% 166M 18s 275350K .......... .......... .......... .......... .......... 51% 28.0M 18s 275400K .......... .......... .......... .......... .......... 51% 186M 18s 275450K .......... .......... .......... .......... .......... 51% 570K 18s 275500K .......... .......... .......... .......... .......... 51% 80.4M 18s 275550K .......... .......... .......... .......... .......... 51% 134M 18s 275600K .......... .......... .......... .......... .......... 51% 25.2M 18s 275650K .......... .......... .......... .......... .......... 51% 89.3M 18s 275700K .......... .......... .......... .......... .......... 51% 130M 18s 275750K .......... .......... .......... .......... .......... 51% 13.4M 18s 275800K .......... .......... 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283000K .......... .......... .......... .......... .......... 53% 167M 17s 283050K .......... .......... .......... .......... .......... 53% 30.4M 17s 283100K .......... .......... .......... .......... .......... 53% 220M 17s 283150K .......... .......... .......... .......... .......... 53% 294M 17s 283200K .......... .......... .......... .......... .......... 53% 253M 17s 283250K .......... .......... .......... .......... .......... 53% 242M 17s 283300K .......... .......... .......... .......... .......... 53% 178M 17s 283350K .......... .......... .......... .......... .......... 53% 230M 17s 283400K .......... .......... .......... .......... .......... 53% 59.3M 17s 283450K .......... .......... .......... .......... .......... 53% 203M 17s 283500K .......... .......... .......... .......... .......... 53% 155M 17s 283550K .......... .......... .......... .......... .......... 53% 234M 17s 283600K .......... .......... .......... .......... .......... 53% 28.5M 17s 283650K 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.......... .......... .......... .......... .......... 53% 56.3M 17s 287600K .......... .......... .......... .......... .......... 53% 83.5M 17s 287650K .......... .......... .......... .......... .......... 53% 132M 17s 287700K .......... .......... .......... .......... .......... 53% 8.31M 17s 287750K .......... .......... .......... .......... .......... 53% 156M 17s 287800K .......... .......... .......... .......... .......... 53% 141M 17s 287850K .......... .......... .......... .......... .......... 53% 125M 17s 287900K .......... .......... .......... .......... .......... 54% 51.1M 17s 287950K .......... .......... .......... .......... .......... 54% 151M 17s 288000K .......... .......... .......... .......... .......... 54% 136M 17s 288050K .......... .......... .......... .......... .......... 54% 180M 17s 288100K .......... .......... .......... .......... .......... 54% 109M 17s 288150K .......... .......... .......... .......... .......... 54% 5.63M 17s 288200K 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349050K .......... .......... .......... .......... .......... 65% 103M 12s 349100K .......... .......... .......... .......... .......... 65% 8.97M 12s 349150K .......... .......... .......... .......... .......... 65% 11.4M 12s 349200K .......... .......... .......... .......... .......... 65% 87.2M 12s 349250K .......... .......... .......... .......... .......... 65% 98.2M 12s 349300K .......... .......... .......... .......... .......... 65% 109M 12s 349350K .......... .......... .......... .......... .......... 65% 84.6M 12s 349400K .......... .......... .......... .......... .......... 65% 81.0M 12s 349450K .......... .......... .......... .......... .......... 65% 6.08M 12s 349500K .......... .......... .......... .......... .......... 65% 116M 12s 349550K .......... .......... .......... .......... .......... 65% 158M 12s 349600K .......... .......... .......... .......... .......... 65% 104M 12s 349650K .......... .......... .......... .......... .......... 65% 4.52M 12s 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350350K .......... .......... .......... .......... .......... 65% 106M 12s 350400K .......... .......... .......... .......... .......... 65% 79.5M 12s 350450K .......... .......... .......... .......... .......... 65% 132M 12s 350500K .......... .......... .......... .......... .......... 65% 88.6M 12s 350550K .......... .......... .......... .......... .......... 65% 123M 12s 350600K .......... .......... .......... .......... .......... 65% 134M 12s 350650K .......... .......... .......... .......... .......... 65% 8.10M 12s 350700K .......... .......... .......... .......... .......... 65% 71.8M 12s 350750K .......... .......... .......... .......... .......... 65% 45.5M 12s 350800K .......... .......... .......... .......... .......... 65% 50.6M 12s 350850K .......... .......... .......... .......... .......... 65% 5.25M 12s 350900K .......... .......... .......... .......... .......... 65% 16.4M 12s 350950K .......... .......... .......... .......... .......... 65% 97.9M 12s 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.......... 78% 26.9M 8s 421000K .......... .......... .......... .......... .......... 78% 91.1M 8s 421050K .......... .......... .......... .......... .......... 78% 6.55M 8s 421100K .......... .......... .......... .......... .......... 78% 118M 8s 421150K .......... .......... .......... .......... .......... 79% 72.6M 8s 421200K .......... .......... .......... .......... .......... 79% 58.9M 8s 421250K .......... .......... .......... .......... .......... 79% 4.26M 8s 421300K .......... .......... .......... .......... .......... 79% 191M 8s 421350K .......... .......... .......... .......... .......... 79% 35.4M 8s 421400K .......... .......... .......... .......... .......... 79% 146M 8s 421450K .......... .......... .......... .......... .......... 79% 58.1M 8s 421500K .......... .......... .......... .......... .......... 79% 8.30M 8s 421550K .......... .......... .......... .......... .......... 79% 66.3M 8s 421600K .......... .......... .......... .......... .......... 79% 117M 8s 421650K .......... .......... .......... .......... .......... 79% 199M 8s 421700K .......... .......... .......... .......... .......... 79% 164M 8s 421750K .......... .......... .......... .......... .......... 79% 5.11M 8s 421800K .......... .......... .......... .......... .......... 79% 137M 8s 421850K .......... .......... .......... .......... .......... 79% 12.6M 8s 421900K .......... .......... .......... .......... .......... 79% 18.7M 8s 421950K .......... .......... .......... .......... .......... 79% 128M 8s 422000K .......... .......... .......... .......... .......... 79% 118M 8s 422050K .......... .......... .......... .......... .......... 79% 18.7M 8s 422100K .......... .......... .......... .......... .......... 79% 11.8M 8s 422150K .......... .......... .......... .......... .......... 79% 131M 8s 422200K .......... .......... .......... .......... .......... 79% 124M 8s 422250K .......... .......... .......... .......... .......... 79% 48.4M 8s 422300K 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.......... 81% 20.0M 7s 435500K .......... .......... .......... .......... .......... 81% 249M 7s 435550K .......... .......... .......... .......... .......... 81% 268M 7s 435600K .......... .......... .......... .......... .......... 81% 25.9M 7s 435650K .......... .......... .......... .......... .......... 81% 90.4M 7s 435700K .......... .......... .......... .......... .......... 81% 161M 7s 435750K .......... .......... .......... .......... .......... 81% 167M 7s 435800K .......... .......... .......... .......... .......... 81% 146M 7s 435850K .......... .......... .......... .......... .......... 81% 143M 7s 435900K .......... .......... .......... .......... .......... 81% 181M 7s 435950K .......... .......... .......... .......... .......... 81% 118M 7s 436000K .......... .......... .......... .......... .......... 81% 18.6M 7s 436050K .......... .......... .......... .......... .......... 81% 124M 7s 436100K .......... .......... .......... .......... .......... 81% 150M 7s 436150K .......... .......... .......... .......... .......... 81% 16.2M 7s 436200K .......... .......... .......... .......... .......... 81% 23.1M 7s 436250K .......... .......... .......... .......... .......... 81% 126M 7s 436300K .......... .......... .......... .......... .......... 81% 205M 7s 436350K .......... .......... .......... .......... .......... 81% 192M 7s 436400K .......... .......... .......... .......... .......... 81% 150M 7s 436450K .......... .......... .......... .......... .......... 81% 55.4M 7s 436500K .......... .......... .......... .......... .......... 81% 28.3M 7s 436550K .......... .......... .......... .......... .......... 81% 14.4M 7s 436600K .......... .......... .......... .......... .......... 81% 17.3M 7s 436650K .......... .......... .......... .......... .......... 81% 22.6M 7s 436700K .......... .......... .......... .......... .......... 81% 38.5M 7s 436750K .......... .......... .......... .......... .......... 81% 27.7M 7s 436800K 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82% 11.9M 7s 440100K .......... .......... .......... .......... .......... 82% 34.9M 7s 440150K .......... .......... .......... .......... .......... 82% 51.7M 7s 440200K .......... .......... .......... .......... .......... 82% 15.5M 7s 440250K .......... .......... .......... .......... .......... 82% 22.7M 7s 440300K .......... .......... .......... .......... .......... 82% 60.9M 7s 440350K .......... .......... .......... .......... .......... 82% 882K 7s 440400K .......... .......... .......... .......... .......... 82% 31.4M 7s 440450K .......... .......... .......... .......... .......... 82% 57.8M 7s 440500K .......... .......... .......... .......... .......... 82% 27.1M 7s 440550K .......... .......... .......... .......... .......... 82% 21.4M 7s 440600K .......... .......... .......... .......... .......... 82% 120M 7s 440650K .......... .......... .......... .......... .......... 82% 161M 7s 440700K .......... .......... .......... .......... .......... 82% 35.7M 7s 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.......... .......... .......... .......... 89% 97.9M 4s 479050K .......... .......... .......... .......... .......... 89% 215M 4s 479100K .......... .......... .......... .......... .......... 89% 197M 4s 479150K .......... .......... .......... .......... .......... 89% 184M 4s 479200K .......... .......... .......... .......... .......... 89% 7.94M 4s 479250K .......... .......... .......... .......... .......... 89% 6.04M 4s 479300K .......... .......... .......... .......... .......... 89% 83.2M 4s 479350K .......... .......... .......... .......... .......... 89% 84.0M 4s 479400K .......... .......... .......... .......... .......... 89% 168M 4s 479450K .......... .......... .......... .......... .......... 89% 11.3M 4s 479500K .......... .......... .......... .......... .......... 89% 115M 4s 479550K .......... .......... .......... .......... .......... 89% 48.8M 4s 479600K .......... .......... .......... .......... .......... 89% 63.6M 4s 479650K .......... .......... .......... .......... .......... 89% 26.1M 4s 479700K .......... .......... .......... .......... .......... 89% 35.1M 4s 479750K .......... .......... .......... .......... .......... 89% 7.50M 4s 479800K .......... .......... .......... .......... .......... 90% 45.6M 4s 479850K .......... .......... .......... .......... .......... 90% 52.4M 4s 479900K .......... .......... .......... .......... .......... 90% 59.8M 4s 479950K .......... .......... .......... .......... .......... 90% 134M 4s 480000K .......... .......... .......... .......... .......... 90% 168M 4s 480050K .......... .......... .......... .......... .......... 90% 9.33M 4s 480100K .......... .......... .......... .......... .......... 90% 46.1M 4s 480150K .......... .......... .......... .......... .......... 90% 51.8M 4s 480200K .......... .......... .......... .......... .......... 90% 112M 4s 480250K .......... .......... .......... .......... .......... 90% 53.8M 4s 480300K .......... .......... .......... 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.......... 90% 52.2M 4s 481000K .......... .......... .......... .......... .......... 90% 27.0M 4s 481050K .......... .......... .......... .......... .......... 90% 109M 4s 481100K .......... .......... .......... .......... .......... 90% 37.4M 4s 481150K .......... .......... .......... .......... .......... 90% 131M 4s 481200K .......... .......... .......... .......... .......... 90% 142M 4s 481250K .......... .......... .......... .......... .......... 90% 54.9M 4s 481300K .......... .......... .......... .......... .......... 90% 43.3M 4s 481350K .......... .......... .......... .......... .......... 90% 75.9M 4s 481400K .......... .......... .......... .......... .......... 90% 76.9M 4s 481450K .......... .......... .......... .......... .......... 90% 69.7M 4s 481500K .......... .......... .......... .......... .......... 90% 109M 4s 481550K .......... .......... .......... .......... .......... 90% 87.2M 4s 481600K .......... .......... .......... .......... .......... 90% 110M 4s 481650K .......... .......... .......... .......... .......... 90% 49.4M 4s 481700K .......... .......... .......... .......... .......... 90% 72.9M 4s 481750K .......... .......... .......... .......... .......... 90% 24.1M 4s 481800K .......... .......... .......... .......... .......... 90% 45.0M 4s 481850K .......... .......... .......... .......... .......... 90% 42.4M 4s 481900K .......... .......... .......... .......... .......... 90% 60.7M 4s 481950K .......... .......... .......... .......... .......... 90% 16.3M 4s 482000K .......... .......... .......... .......... .......... 90% 31.5M 4s 482050K .......... .......... .......... .......... .......... 90% 130M 4s 482100K .......... .......... .......... .......... .......... 90% 6.16M 4s 482150K .......... .......... .......... .......... .......... 90% 49.0M 4s 482200K .......... .......... .......... .......... .......... 90% 59.8M 4s 482250K .......... .......... .......... .......... .......... 90% 17.8M 4s 482300K .......... .......... .......... .......... .......... 90% 83.3M 4s 482350K .......... .......... .......... .......... .......... 90% 2.77M 4s 482400K .......... .......... .......... .......... .......... 90% 78.8M 4s 482450K .......... .......... .......... .......... .......... 90% 92.7M 4s 482500K .......... .......... .......... .......... .......... 90% 140M 4s 482550K .......... .......... .......... .......... .......... 90% 21.9M 4s 482600K .......... .......... .......... .......... .......... 90% 130M 4s 482650K .......... .......... .......... .......... .......... 90% 148M 4s 482700K .......... .......... .......... .......... .......... 90% 123M 4s 482750K .......... .......... .......... .......... .......... 90% 24.6M 4s 482800K .......... .......... .......... .......... .......... 90% 132M 4s 482850K .......... .......... .......... .......... .......... 90% 35.2M 4s 482900K .......... .......... .......... .......... .......... 90% 131M 4s 482950K .......... 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.......... .......... .......... 90% 14.2M 4s 483650K .......... .......... .......... .......... .......... 90% 17.1M 4s 483700K .......... .......... .......... .......... .......... 90% 23.7M 4s 483750K .......... .......... .......... .......... .......... 90% 62.6M 4s 483800K .......... .......... .......... .......... .......... 90% 83.9M 4s 483850K .......... .......... .......... .......... .......... 90% 68.5M 4s 483900K .......... .......... .......... .......... .......... 90% 111M 4s 483950K .......... .......... .......... .......... .......... 90% 94.4M 4s 484000K .......... .......... .......... .......... .......... 90% 73.3M 4s 484050K .......... .......... .......... .......... .......... 90% 99.6M 4s 484100K .......... .......... .......... .......... .......... 90% 2.49M 4s 484150K .......... .......... .......... .......... .......... 90% 12.4M 4s 484200K .......... .......... .......... .......... .......... 90% 14.7M 4s 484250K .......... .......... .......... 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.......... 90% 66.9M 4s 484950K .......... .......... .......... .......... .......... 90% 47.7M 4s 485000K .......... .......... .......... .......... .......... 90% 61.2M 4s 485050K .......... .......... .......... .......... .......... 90% 95.0M 4s 485100K .......... .......... .......... .......... .......... 90% 185M 4s 485150K .......... .......... .......... .......... .......... 91% 198M 4s 485200K .......... .......... .......... .......... .......... 91% 219M 4s 485250K .......... .......... .......... .......... .......... 91% 237M 4s 485300K .......... .......... .......... .......... .......... 91% 209M 4s 485350K .......... .......... .......... .......... .......... 91% 9.53M 4s 485400K .......... .......... .......... .......... .......... 91% 4.30M 4s 485450K .......... .......... .......... .......... .......... 91% 6.78M 4s 485500K .......... .......... .......... .......... .......... 91% 7.27M 4s 485550K .......... .......... .......... .......... .......... 91% 1.53M 4s 485600K .......... .......... .......... .......... .......... 91% 114M 4s 485650K .......... .......... .......... .......... .......... 91% 10.8M 4s 485700K .......... .......... .......... .......... .......... 91% 8.18M 4s 485750K .......... .......... .......... .......... .......... 91% 95.7M 4s 485800K .......... .......... .......... .......... .......... 91% 5.48M 3s 485850K .......... .......... .......... .......... .......... 91% 93.7M 3s 485900K .......... .......... .......... .......... .......... 91% 153M 3s 485950K .......... .......... .......... .......... .......... 91% 61.7M 3s 486000K .......... .......... .......... .......... .......... 91% 32.9M 3s 486050K .......... .......... .......... .......... .......... 91% 45.0M 3s 486100K .......... .......... .......... .......... .......... 91% 34.7M 3s 486150K .......... .......... .......... .......... .......... 91% 144M 3s 486200K .......... .......... .......... .......... .......... 91% 11.9M 3s 486250K .......... .......... .......... .......... .......... 91% 103M 3s 486300K .......... .......... .......... .......... .......... 91% 111M 3s 486350K .......... .......... .......... .......... .......... 91% 6.19M 3s 486400K .......... .......... .......... .......... .......... 91% 42.7M 3s 486450K .......... .......... .......... .......... .......... 91% 30.2M 3s 486500K .......... .......... .......... .......... .......... 91% 3.68M 3s 486550K .......... .......... .......... .......... .......... 91% 41.5M 3s 486600K .......... .......... .......... .......... .......... 91% 36.8M 3s 486650K .......... .......... .......... .......... .......... 91% 40.1M 3s 486700K .......... .......... .......... .......... .......... 91% 6.71M 3s 486750K .......... .......... .......... .......... .......... 91% 90.4M 3s 486800K .......... .......... .......... .......... .......... 91% 37.3M 3s 486850K .......... .......... .......... .......... .......... 91% 7.44M 3s 486900K .......... .......... .......... .......... .......... 91% 43.6M 3s 486950K .......... .......... .......... .......... .......... 91% 20.2M 3s 487000K .......... .......... .......... .......... .......... 91% 6.31M 3s 487050K .......... .......... .......... .......... .......... 91% 131M 3s 487100K .......... .......... .......... .......... .......... 91% 34.5M 3s 487150K .......... .......... .......... .......... .......... 91% 21.5M 3s 487200K .......... .......... .......... .......... .......... 91% 6.87M 3s 487250K .......... .......... .......... .......... .......... 91% 213M 3s 487300K .......... .......... .......... .......... .......... 91% 75.5M 3s 487350K .......... .......... .......... .......... .......... 91% 7.43M 3s 487400K .......... .......... .......... .......... .......... 91% 24.5M 3s 487450K .......... .......... .......... .......... .......... 91% 38.8M 3s 487500K .......... .......... .......... .......... .......... 91% 6.77M 3s 487550K .......... 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.......... .......... 91% 6.67M 3s 488900K .......... .......... .......... .......... .......... 91% 131M 3s 488950K .......... .......... .......... .......... .......... 91% 66.8M 3s 489000K .......... .......... .......... .......... .......... 91% 103M 3s 489050K .......... .......... .......... .......... .......... 91% 5.73M 3s 489100K .......... .......... .......... .......... .......... 91% 81.8M 3s 489150K .......... .......... .......... .......... .......... 91% 212M 3s 489200K .......... .......... .......... .......... .......... 91% 5.82M 3s 489250K .......... .......... .......... .......... .......... 91% 39.0M 3s 489300K .......... .......... .......... .......... .......... 91% 81.1M 3s 489350K .......... .......... .......... .......... .......... 91% 24.1M 3s 489400K .......... .......... .......... .......... .......... 91% 6.34M 3s 489450K .......... .......... .......... .......... .......... 91% 128M 3s 489500K .......... .......... .......... .......... .......... 91% 36.1M 3s 489550K .......... .......... .......... .......... .......... 91% 6.44M 3s 489600K .......... .......... .......... .......... .......... 91% 71.6M 3s 489650K .......... .......... .......... .......... .......... 91% 83.6M 3s 489700K .......... .......... .......... .......... .......... 91% 40.6M 3s 489750K .......... .......... .......... .......... .......... 91% 6.39M 3s 489800K .......... .......... .......... .......... .......... 91% 50.4M 3s 489850K .......... .......... .......... .......... .......... 91% 38.2M 3s 489900K .......... .......... .......... .......... .......... 91% 6.23M 3s 489950K .......... .......... .......... .......... .......... 91% 89.4M 3s 490000K .......... .......... .......... .......... .......... 91% 73.5M 3s 490050K .......... .......... .......... .......... .......... 91% 18.1M 3s 490100K .......... .......... .......... .......... .......... 91% 6.37M 3s 490150K .......... .......... .......... .......... .......... 91% 35.8M 3s 490200K .......... .......... .......... .......... .......... 91% 24.4M 3s 490250K .......... .......... .......... .......... .......... 91% 5.89M 3s 490300K .......... .......... .......... .......... .......... 91% 104M 3s 490350K .......... .......... .......... .......... .......... 91% 35.5M 3s 490400K .......... .......... .......... .......... .......... 91% 61.0M 3s 490450K .......... .......... .......... .......... .......... 91% 5.65M 3s 490500K .......... .......... .......... .......... .......... 92% 104M 3s 490550K .......... .......... .......... .......... .......... 92% 49.6M 3s 490600K .......... .......... .......... .......... .......... 92% 6.65M 3s 490650K .......... .......... .......... .......... .......... 92% 52.2M 3s 490700K .......... .......... .......... .......... .......... 92% 43.1M 3s 490750K .......... .......... .......... .......... .......... 92% 85.8M 3s 490800K .......... .......... .......... .......... .......... 92% 6.32M 3s 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.......... .......... .......... .......... .......... 92% 62.5M 3s 491550K .......... .......... .......... .......... .......... 92% 7.34M 3s 491600K .......... .......... .......... .......... .......... 92% 93.5M 3s 491650K .......... .......... .......... .......... .......... 92% 127M 3s 491700K .......... .......... .......... .......... .......... 92% 6.66M 3s 491750K .......... .......... .......... .......... .......... 92% 47.4M 3s 491800K .......... .......... .......... .......... .......... 92% 75.5M 3s 491850K .......... .......... .......... .......... .......... 92% 3.57M 3s 491900K .......... .......... .......... .......... .......... 92% 2.47M 3s 491950K .......... .......... .......... .......... .......... 92% 62.7M 3s 492000K .......... .......... .......... .......... .......... 92% 43.5M 3s 492050K .......... .......... .......... .......... .......... 92% 63.2M 3s 492100K .......... .......... .......... .......... .......... 92% 5.81M 3s 492150K .......... 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6.43M 3s 494800K .......... .......... .......... .......... .......... 92% 178M 3s 494850K .......... .......... .......... .......... .......... 92% 180M 3s 494900K .......... .......... .......... .......... .......... 92% 173M 3s 494950K .......... .......... .......... .......... .......... 92% 5.84M 3s 495000K .......... .......... .......... .......... .......... 92% 44.2M 3s 495050K .......... .......... .......... .......... .......... 92% 206M 3s 495100K .......... .......... .......... .......... .......... 92% 158M 3s 495150K .......... .......... .......... .......... .......... 92% 6.62M 3s 495200K .......... .......... .......... .......... .......... 92% 77.5M 3s 495250K .......... .......... .......... .......... .......... 92% 137M 3s 495300K .......... .......... .......... .......... .......... 92% 203M 3s 495350K .......... .......... .......... .......... .......... 92% 3.96M 3s 495400K .......... .......... .......... .......... .......... 92% 139M 3s 495450K 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3s 498100K .......... .......... .......... .......... .......... 93% 75.7M 3s 498150K .......... .......... .......... .......... .......... 93% 162M 3s 498200K .......... .......... .......... .......... .......... 93% 6.56M 3s 498250K .......... .......... .......... .......... .......... 93% 182M 3s 498300K .......... .......... .......... .......... .......... 93% 164M 3s 498350K .......... .......... .......... .......... .......... 93% 118M 3s 498400K .......... .......... .......... .......... .......... 93% 106M 3s 498450K .......... .......... .......... .......... .......... 93% 5.96M 3s 498500K .......... .......... .......... .......... .......... 93% 98.4M 3s 498550K .......... .......... .......... .......... .......... 93% 129M 3s 498600K .......... .......... .......... .......... .......... 93% 116M 3s 498650K .......... .......... .......... .......... .......... 93% 5.65M 3s 498700K .......... .......... .......... .......... .......... 93% 46.0M 3s 498750K 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.......... 95% 76.5M 2s 507350K .......... .......... .......... .......... .......... 95% 64.2M 2s 507400K .......... .......... .......... .......... .......... 95% 101M 2s 507450K .......... .......... .......... .......... .......... 95% 7.85M 2s 507500K .......... .......... .......... .......... .......... 95% 76.8M 2s 507550K .......... .......... .......... .......... .......... 95% 109M 2s 507600K .......... .......... .......... .......... .......... 95% 65.5M 2s 507650K .......... .......... .......... .......... .......... 95% 4.94M 2s 507700K .......... .......... .......... .......... .......... 95% 77.5M 2s 507750K .......... .......... .......... .......... .......... 95% 69.9M 2s 507800K .......... .......... .......... .......... .......... 95% 113M 2s 507850K .......... .......... .......... .......... .......... 95% 99.0M 2s 507900K .......... .......... .......... .......... .......... 95% 6.39M 2s 507950K .......... .......... .......... .......... .......... 95% 2.88M 2s 508000K .......... .......... .......... .......... .......... 95% 7.13M 2s 508050K .......... .......... .......... .......... .......... 95% 62.0M 2s 508100K .......... .......... .......... .......... .......... 95% 86.6M 2s 508150K .......... .......... .......... .......... .......... 95% 95.4M 2s 508200K .......... .......... .......... .......... .......... 95% 15.9M 2s 508250K .......... .......... .......... .......... .......... 95% 176M 2s 508300K .......... .......... .......... .......... .......... 95% 211M 2s 508350K .......... .......... .......... .......... .......... 95% 72.7M 2s 508400K .......... .......... .......... .......... .......... 95% 99.2M 2s 508450K .......... .......... .......... .......... .......... 95% 178M 2s 508500K .......... .......... .......... .......... .......... 95% 205M 2s 508550K .......... .......... .......... .......... .......... 95% 161M 2s 508600K .......... .......... .......... .......... .......... 95% 111M 2s 508650K 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.......... .......... .......... .......... .......... 99% 126M 0s 533100K .......... .......... .......... .......... .......... 99% 135M 0s 533150K ......... 100% 162M=39s 2024-07-28 00:47:09 (13.5 MB/s) - ‘ESP126-macos-x86_64.tgz’ saved [545954930/545954930] + tar -xf ESP126-macos-x86_64.tgz + cd ESP126 + rm -rf /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Slugs ++ uname -a + [[ Darwin macys-VM 20.6.0 Darwin Kernel Version 20.6.0: Thu Sep 29 20:15:11 PDT 2022; root:xnu-7195.141.42~1/RELEASE_X86_64 x86_64 == *\D\a\r\w\i\n* ]] + ./setup.command Custom icon assigned to '/Users/jenkins/Desktop/ESP126.command' based on '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/ESP/esp_logo.png'. Custom icon assigned to '/Users/jenkins/Desktop/runESP126.command' based on '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/ESP/esp_logo.png'. Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/idle3.11' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/pyftsubset' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/test_op4' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/ttx' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/wingproj' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/test_op2' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/pip3' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/test_bdf' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/imageio_remove_bin' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/undill' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/bdf' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/run_om_test' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/f90nml' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/webview' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/fonttools' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/openmdao' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/pyNastranGUI' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/f2py' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/pydoc3.11' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/2to3-3.11' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/imageio_download_bin' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/pip3.11' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/test_pynastrangui' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/numba' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/normalizer' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/virtualenv' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/reset_notebook' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/abaqus_to_nastran' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/get_gprof' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/format_converter' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/pyftmerge' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/python3.11-config' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/f06' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/get_objgraph' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib/python3.11/config-3.11-darwin/Makefile' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib/python3.11/config-3.11-darwin/python-config.py' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib/pkgconfig/python-3.11-embed.pc' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib/pkgconfig/python-3.11.pc' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib/python3.11/_sysconfigdata__darwin_darwin.py' Patching '/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib/python3.11/site-packages/mpi4py/mpi.cfg' Patching 'bin/mpirun_esp' Patching 'bin/ompi_info' Patching 'bin/pmix_info' Patching 'bin/prte_info' Patching 'lib/libmpi.40.dylib' Patching 'lib/libopen-pal.80.dylib' Patching 'lib/libpmix.2.dylib' Patching 'lib/libprrte.3.dylib' Patching 'lib/openmpi/mca_io_romio341.so' Patching 'lib/prte/prte_mca_schizo_ompi.so' Patching 'include/pmix/src/include/pmix_config.h' Patching 'lib/pkgconfig/ompi-c.pc' Patching 'lib/pkgconfig/ompi-cxx.pc' Patching 'lib/pkgconfig/ompi-fort.pc' Patching 'lib/pkgconfig/ompi.pc' Patching 'lib/pkgconfig/pmix.pc' Patching 'share/openmpi/mpic++-wrapper-data.txt' Patching 'share/openmpi/mpicc-wrapper-data.txt' Patching 'share/openmpi/mpifort-wrapper-data.txt' Patching 'share/pmix/pmixcc-wrapper-data.txt' + rm -rf /Users/jenkins/Desktop/ESP126.command /Users/jenkins/Desktop/runESP126.command + source /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/ESPenv.sh ++ export ESP_ARCH=DARWIN64 ++ ESP_ARCH=DARWIN64 ++ export ESP_ROOT=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad ++ ESP_ROOT=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad ++ export CASROOT=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/OpenCASCADE-7.8.1 ++ CASROOT=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/OpenCASCADE-7.8.1 ++ export CASARCH=. ++ CASARCH=. ++ export CASREV=7.8 ++ CASREV=7.8 ++ '[' -z /Users/jenkins/workspace/ESP_bPreBuilt/ESP//test:/Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin:/Users/jenkins/util/tsfoil:/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ']' ++ export PATH=.:/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin:/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin:/Users/jenkins/workspace/ESP_bPreBuilt/ESP//test:/Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin:/Users/jenkins/util/tsfoil:/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PATH=.:/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin:/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin:/Users/jenkins/workspace/ESP_bPreBuilt/ESP//test:/Users/jenkins/workspace/ESP_bPreBuilt/ESP//bin:/Users/jenkins/util/tsfoil:/Users/jenkins/util/refine/build_parallel/install/bin:/Users/jenkins/util/delaundo/delaundo/src:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin:/Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC/:/Users/jenkins/util/astros/Astros/Darwin-64bit:/usr/local/bin:/usr/local/opt/python/libexec/bin:/opt/intel/oneapi/dev-utilities/2021.3.0/bin:/opt/intel/oneapi/compiler/2021.3.0/mac/bin/intel64:/usr/bin:/bin:/usr/sbin:/sbin:/usr/local/bin/:/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ export PYTHONINC=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/include/python3.11 ++ PYTHONINC=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/include/python3.11 ++ export 'PYTHONLIB=-L/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib -lpython3.11' ++ PYTHONLIB='-L/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib -lpython3.11' ++ '[' -z /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/pyCAPS:/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/pyOCSM:/Users/jenkins/workspace/ESP_bPreBuilt/EGADS/trunk/pyEGADS::/Users/jenkins/util/SU2/SU2-v8.0.1/bin ']' ++ export PYTHONPATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/lib:/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/pyESP:/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib/python3.11/site-packages:/Users/jenkins/workspace/ESP_bPreBuilt/CAPS/pyCAPS:/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/pyOCSM:/Users/jenkins/workspace/ESP_bPreBuilt/EGADS/trunk/pyEGADS::/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ PYTHONPATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/lib:/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/pyESP:/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib/python3.11/site-packages:/Users/jenkins/workspace/ESP_bPreBuilt/CAPS/pyCAPS:/Users/jenkins/workspace/ESP_bPreBuilt/OpenCSM/trunk/pyOCSM:/Users/jenkins/workspace/ESP_bPreBuilt/EGADS/trunk/pyEGADS::/Users/jenkins/util/SU2/SU2-v8.0.1/bin ++ export UDUNITS2_XML_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/src/CAPS/udunits/udunits2.xml ++ UDUNITS2_XML_PATH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/src/CAPS/udunits/udunits2.xml ++ export CAPS_GLYPH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/src/CAPS/aim/pointwise/glyph ++ CAPS_GLYPH=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/src/CAPS/aim/pointwise/glyph ++ export 'SLUGS_START=open -a /Applications/Safari.app /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/SLUGS/Slugs.html' ++ SLUGS_START='open -a /Applications/Safari.app /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/SLUGS/Slugs.html' ++ export 'ESP_START=open -a /Applications/Safari.app;sleep 1;open -a /Applications/Safari.app /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/ESP/ESP-localhost7681.html' ++ ESP_START='open -a /Applications/Safari.app;sleep 1;open -a /Applications/Safari.app /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/ESP/ESP-localhost7681.html' ++ export 'WV_START=open -a /Applications/Safari.app /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/wvClient/wv.html' ++ WV_START='open -a /Applications/Safari.app /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/wvClient/wv.html' + which python /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/python + python --version Python 3.11.9 + export CSMDATA=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data + CSMDATA=/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data + cd /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin ++ uname -a + [[ Darwin macys-VM 20.6.0 Darwin Kernel Version 20.6.0: Thu Sep 29 20:15:11 PDT 2022; root:xnu-7195.141.42~1/RELEASE_X86_64 x86_64 == *\D\a\r\w\i\n* ]] + sed -i '' '/.*capsExamples.*/d' /Users/jenkins/workspace/ESP_bPreBuilt/Verification.sh + bash -ex /Users/jenkins/workspace/ESP_bPreBuilt/Verification.sh + expectSuccess 01 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/expressions + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/expressions WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/verify_7.8.1/expressions.vfy", so verification is being skipped ERROR:: problem evaluating argument 2 (slice(e3,0,999)) for Branch 152 (set) ERROR:: problem evaluating argument 2 (slice(e3,14,999)) for Branch 158 (set) ERROR:: problem evaluating argument 2 (slice(e3,4,-1)) for Branch 164 (set) ==> serveESP completed successfully with no verification data real 0m4.315s user 0m0.033s sys 0m0.021s + set +x ============================================= ESP verification case 01 passed (as expected) ============================================= + expectSuccess 02 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/demo2 + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/demo2 WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/verify_7.8.1/demo2.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.245s user 0m0.291s sys 0m0.038s + set +x ============================================= ESP verification case 02 passed (as expected) ============================================= + expectSuccess 03 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/legacy/tutorial1_whole + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/legacy/tutorial1_whole WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/legacy/verify_7.8.1/tutorial1_whole.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m2.813s user 0m4.145s sys 0m0.762s + set +x ============================================= ESP verification case 03 passed (as expected) ============================================= + expectSuccess 04 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/design2 + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/design2 WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/verify_7.8.1/design2.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.693s user 0m0.769s sys 0m0.045s + set +x ============================================= ESP verification case 04 passed (as expected) ============================================= + expectSuccess 05 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/design3 + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/design3 WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/verify_7.8.1/design3.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.648s user 0m0.878s sys 0m0.064s + set +x ============================================= ESP verification case 05 passed (as expected) ============================================= + expectSuccess 06 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/legacy/tutorial2 + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/legacy/tutorial2 WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/legacy/verify_7.8.1/tutorial2.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.716s user 0m0.912s sys 0m0.064s + set +x ============================================= ESP verification case 06 passed (as expected) ============================================= + expectSuccess 07 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/legacy/tutorial3 + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/legacy/tutorial3 WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/legacy/verify_7.8.1/tutorial3.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m3.784s user 0m5.594s sys 0m0.427s + set +x ============================================= ESP verification case 07 passed (as expected) ============================================= + expectSuccess 08 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/CAPS/myPlane + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/CAPS/myPlane WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/CAPS/verify_7.8.1/myPlane.vfy", so verification is being skipped ==> serveESP completed successfully with 12 warnings and no verification data real 0m35.664s user 0m49.219s sys 0m2.054s + set +x ============================================= ESP verification case 08 passed (as expected) ============================================= + expectSuccess 09 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/bottle + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/bottle WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/verify_7.8.1/bottle.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.665s user 0m0.812s sys 0m0.034s + set +x ============================================= ESP verification case 09 passed (as expected) ============================================= + expectSuccess 10 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/wingMultiModel + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/wingMultiModel WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/verify_7.8.1/wingMultiModel.vfy", so verification is being skipped ==> serveESP completed successfully with 4 warnings and no verification data real 0m42.765s user 1m12.680s sys 0m5.177s + set +x ============================================= ESP verification case 10 passed (as expected) ============================================= + expectSuccess 11 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/bullet + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/bullet WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/verify_7.8.1/bullet.vfy", so verification is being skipped WARNING:: 8 _hist and/or __trace__ attributes removed WARNING:: 8 _hist and/or __trace__ attributes removed WARNING:: could not find mapping for iedge=10 WARNING:: could not find mapping for iedge=14 WARNING:: could not find mapping for iedge=7 WARNING:: could not find mapping for iedge=11 ==> serveESP completed successfully with 4 warnings and no verification data real 0m0.512s user 0m0.280s sys 0m0.037s + set +x ============================================= ESP verification case 11 passed (as expected) ============================================= + expectSuccess 12 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/connect5 + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/connect5 WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/verify_7.8.1/connect5.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.527s user 0m0.780s sys 0m0.026s + set +x ============================================= ESP verification case 12 passed (as expected) ============================================= + expectSuccess 13 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/group2 + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/group2 WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/verify_7.8.1/group2.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.172s user 0m0.211s sys 0m0.021s + set +x ============================================= ESP verification case 13 passed (as expected) ============================================= + expectSuccess 14 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/csm3 + ./serveESP -batch -verify -outLevel 0 /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/csm3 WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/basic/verify_7.8.1/csm3.vfy", so verification is being skipped nnode=8 nedge=12 nface=6 nnode=8 nedge=12 nface=6 nnode=16 nedge=24 nface=10 nnode=8 nedge=12 nface=6 ==> serveESP completed successfully with no verification data real 0m0.437s user 0m0.497s sys 0m0.029s + set +x ============================================= ESP verification case 14 passed (as expected) ============================================= + cd /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/pyESP/testEGADS + make test python --version Python 3.11.9 python -u -m unittest discover ...................................................... PCurve Map: 48 (alloc 48)! Surface Map: 12 (alloc 24)! Curve Map: 28 (alloc 28)! Writing PCurves... Writing Curves... Writing Surfaces... Writing 16 Nodes... Writing 28 Edges... Writing 12 Loops... Writing 12 Faces... Writing 1 Shells... EGADS Info: 0 Objects, 0 Reference in Use (of 972) at Close! ................... ---------------------------------------------------------------------- Ran 73 tests in 2.864s OK + cd /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/pyESP/testOCSM + source /Users/jenkins/workspace/ESP_bPreBuilt/JenkinsESP/test_pyOCSM.sh ++ set -x ++ python -u test_pyOCSM.py -skipHelp real 0m8.450s user 0m11.251s sys 0m0.312s ++ set +x ================================================= test_pyOCSM.py passed (as expected) ================================================= + cd /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/pyESP/testCAPS + make test python --version Python 3.11.9 python -u -m unittest discover ..Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = Upper_Left, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing1, index = 1 Name = Wing2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 143 Number of elements = 282 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 282 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 155 Number of elements = 306 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 306 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 298 Combined Number of elements = 588 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 588 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Wing1 Property name - Wing2 Done getting FEA properties Updating mesh element types based on properties input ... EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! ..Writing D3 Javascript library - d3.v3.min.js ........... EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! .No analysis directory provided - defaulting to altName Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = Upper_Left, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing1, index = 1 Name = Wing2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 209 Number of elements = 414 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 414 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 186 Number of elements = 368 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 368 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 395 Combined Number of elements = 782 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 782 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Wing1 Property name - Wing2 Done getting FEA properties Updating mesh element types based on properties input ..........--> Opening DESPMTR file "unitGeom.param" updating CFGPMTR series [ 1, 1] = 8412.000000 updating CFGPMTR series2 [ 1, 1] = 20.000000 updating CFGPMTR VIEW:CFD [ 1, 1] = 1.000000 updating CFGPMTR nrow [ 1, 1] = 3.000000 updating CFGPMTR ncol [ 1, 1] = 2.000000 updating DESPMTR area [ 1, 1] = 40.000000 updating DESPMTR aspect [ 1, 1] = 5.000000 updating DESPMTR taper [ 1, 1] = 0.500000 updating DESPMTR twist [ 1, 1] = 15.000000 updating DESPMTR wing:lesweep [ 1, 1] = 30.000000 updating DESPMTR wing:dihedral [ 1, 1] = 1.000000 updating DESPMTR wing:chord:root [ 1, 1] = 1.560000 updating DESPMTR htail [ 1, 1] = 1.000000 updating DESPMTR htail:chord [ 1, 1] = 2.000000 updating DESPMTR vtail:chord [ 1, 1] = 3.000000 updating DESPMTR vtail [ 1, 1] = 4.000000 updating DESPMTR sphereR [ 1, 1] = 80.000000 updating DESPMTR v@1:d_name [ 1, 1] = 1.000000 updating DESPMTR despMat [ 1, 1] = 11.000000 updating DESPMTR despMat [ 1, 2] = 12.000000 updating DESPMTR despMat [ 2, 1] = 13.000000 updating DESPMTR despMat [ 2, 2] = 14.000000 updating DESPMTR despMat [ 3, 1] = 15.000000 updating DESPMTR despMat [ 3, 2] = 16.000000 updating DESPMTR despCol [ 1, 1] = 11.000000 updating DESPMTR despCol [ 2, 1] = 13.000000 updating DESPMTR despCol [ 3, 1] = 15.000000 updating DESPMTR despRow [ 1, 1] = 11.000000 updating DESPMTR despRow [ 1, 2] = 12.000000 updating DESPMTR despRow [ 1, 3] = 13.000000 ERROR:: DESPMTR file "unitGeom.param" not found CAPS Error: ocsmSaveDespmtrs = -201 (caps_readParameters)! EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! .. EGADS Error: No Attribute -> __numRemaining__ (EG_attributeDel)! EGADS Error: No Attribute -> __numRemaining__ (EG_attributeDel)! EGADS Error: No Attribute -> _body (EG_attributeDel)! EGADS Error: No Attribute -> _nface (EG_attributeDel)! EGADS Error: No Attribute -> __trace__ (EG_attributeDel)! EGADS Error: No Attribute -> _body (EG_attributeDel)! EGADS Error: No Attribute -> _nface (EG_attributeDel)! EGADS Error: No Attribute -> __trace__ (EG_attributeDel)! EGADS Error: No Attribute -> _body (EG_attributeDel)! EGADS Error: No Attribute -> _nface (EG_attributeDel)! EGADS Error: No Attribute -> __trace__ (EG_attributeDel)! EGADS Error: No Attribute -> _body (EG_attributeDel)! EGADS Error: No Attribute -> _nface (EG_attributeDel)! EGADS Error: No Attribute -> __trace__ (EG_attributeDel)! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! .. EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! ..Linked Parameter Beta to analysis su2 input Beta Linked Parameter Alpha to analysis su2 input Alpha No linkable data found for Altitude No linkable data found for Strings No linkable data found for Strings2 Linked Parameter Beta to analysis su2 input Beta Linked Parameter Alpha to analysis su2 input Alpha ............ EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! .. EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . CAPS Info: Hit last success -- going live! ... EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! .. EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! .. EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! .. EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! .. EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Error: No Attribute -> __numRemaining__ (EG_attributeDel)! EGADS Error: No Attribute -> _body (EG_attributeDel)! EGADS Error: No Attribute -> _nface (EG_attributeDel)! EGADS Error: No Attribute -> __trace__ (EG_attributeDel)! EGADS Error: No Attribute -> _body (EG_attributeDel)! EGADS Error: No Attribute -> _nface (EG_attributeDel)! EGADS Error: No Attribute -> __trace__ (EG_attributeDel)! EGADS Error: No Attribute -> _body (EG_attributeDel)! EGADS Error: No Attribute -> _nface (EG_attributeDel)! EGADS Error: No Attribute -> __trace__ (EG_attributeDel)! EGADS Error: No Attribute -> _body (EG_attributeDel)! EGADS Error: No Attribute -> _nface (EG_attributeDel)! EGADS Error: No Attribute -> __trace__ (EG_attributeDel)! EGADS Error: No Attribute -> __numRemaining__ (EG_attributeDel)! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! .--> Opening DESPMTR file "unitGeom.param" updating CFGPMTR series [ 1, 1] = 8412.000000 updating CFGPMTR series2 [ 1, 1] = 20.000000 updating CFGPMTR VIEW:CFD [ 1, 1] = 1.000000 updating CFGPMTR nrow [ 1, 1] = 3.000000 updating CFGPMTR ncol [ 1, 1] = 2.000000 updating DESPMTR area [ 1, 1] = 40.000000 updating DESPMTR aspect [ 1, 1] = 5.000000 updating DESPMTR taper [ 1, 1] = 0.500000 updating DESPMTR twist [ 1, 1] = 15.000000 updating DESPMTR wing:lesweep [ 1, 1] = 30.000000 updating DESPMTR wing:dihedral [ 1, 1] = 1.000000 updating DESPMTR wing:chord:root [ 1, 1] = 1.560000 updating DESPMTR htail [ 1, 1] = 1.000000 updating DESPMTR htail:chord [ 1, 1] = 2.000000 updating DESPMTR vtail:chord [ 1, 1] = 3.000000 updating DESPMTR vtail [ 1, 1] = 4.000000 updating DESPMTR sphereR [ 1, 1] = 80.000000 updating DESPMTR v@1:d_name [ 1, 1] = 1.000000 updating DESPMTR despMat [ 1, 1] = 11.000000 updating DESPMTR despMat [ 1, 2] = 12.000000 updating DESPMTR despMat [ 2, 1] = 13.000000 updating DESPMTR despMat [ 2, 2] = 14.000000 updating DESPMTR despMat [ 3, 1] = 15.000000 updating DESPMTR despMat [ 3, 2] = 16.000000 updating DESPMTR despCol [ 1, 1] = 11.000000 updating DESPMTR despCol [ 2, 1] = 13.000000 updating DESPMTR despCol [ 3, 1] = 15.000000 updating DESPMTR despRow [ 1, 1] = 11.000000 updating DESPMTR despRow [ 1, 2] = 12.000000 updating DESPMTR despRow [ 1, 3] = 13.000000 ERROR:: DESPMTR file "unitGeom.param" not found CAPS Error: ocsmSaveDespmtrs = -201 (caps_readParameters)! EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! . EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! ................ EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! ---------------------------------------------------------------------- Ran 100 tests in 40.745s OK WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsGeometry.setGeometryVal' is deprecated. Please use 'Problem.geometry.despmtr["varname"].value'! WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! + cd /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/src/CAPS/aim/unitTest/pyCAPS/ + make test python --version Python 3.11.9 python -u -m unittest discover --verbose test_journal (test_aflr2.TestAFLR2.test_journal) ... Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 2244 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 2244 2244 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 450 902 AFLR2 IG : Nodes, Faces = 900 1802 AFLR2 IG : Nodes, Faces = 1145 2292 AFLR2 IG : Nodes, Faces = 1260 2522 AFLR2 IG : Nodes, Faces = 1350 2702 AFLR2 IG : Nodes, Faces = 1360 2722 AFLR2 IG : Nodes, Faces = 1460 2922 AFLR2 IG : Nodes, Faces = 1560 3122 AFLR2 IG : Nodes, Faces = 1660 3322 AFLR2 IG : Nodes, Faces = 1760 3522 AFLR2 IG : Nodes, Faces = 1800 3602 AFLR2 IG : Nodes, Faces = 1860 3722 AFLR2 IG : Nodes, Faces = 1960 3922 AFLR2 IG : Nodes, Faces = 2060 4122 AFLR2 IG : Nodes, Faces = 2085 4172 AFLR2 IG : Nodes, Faces = 2244 4490 AFLR2 IG : Nodes, Faces = 2248 4490 AFLR2 IG : Nodes, Faces = 2244 2244 AFLR2 : CPU Time = 0.032 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 2244 2244 AFLR2 GG : Nodes, Faces = 4283 6322 AFLR2 GG : Nodes, Faces = 6128 10012 AFLR2 GG : Nodes, Faces = 7863 13482 AFLR2 GG : Nodes, Faces = 9464 16684 AFLR2 GG : Nodes, Faces = 10948 19652 AFLR2 GG : Nodes, Faces = 12322 22400 AFLR2 GG : Nodes, Faces = 13619 24994 AFLR2 GG : Nodes, Faces = 14829 27414 AFLR2 GG : Nodes, Faces = 15981 29718 AFLR2 GG : Nodes, Faces = 17082 31920 AFLR2 GG : Nodes, Faces = 18110 33976 AFLR2 GG : Nodes, Faces = 19081 35918 AFLR2 GG : Nodes, Faces = 20014 37784 AFLR2 GG : Nodes, Faces = 20924 39604 AFLR2 GG : Nodes, Faces = 21782 41320 AFLR2 GG : Nodes, Faces = 22595 42946 AFLR2 GG : Nodes, Faces = 23377 44510 AFLR2 GG : Nodes, Faces = 24129 46014 AFLR2 GG : Nodes, Faces = 24840 47436 AFLR2 GG : Nodes, Faces = 25522 48800 AFLR2 GG : Nodes, Faces = 26170 50096 AFLR2 GG : Nodes, Faces = 26793 51342 AFLR2 GG : Nodes, Faces = 27346 52448 AFLR2 GG : Nodes, Faces = 27846 53448 AFLR2 GG : Nodes, Faces = 28280 54316 AFLR2 GG : Nodes, Faces = 28652 55060 AFLR2 GG : Nodes, Faces = 28920 55596 AFLR2 GG : Nodes, Faces = 29143 56042 AFLR2 GG : Nodes, Faces = 29358 56472 AFLR2 GG : Nodes, Faces = 29550 56856 AFLR2 GG : Nodes, Faces = 29693 57142 AFLR2 GG : Nodes, Faces = 29805 57366 AFLR2 GG : Nodes, Faces = 29875 57506 AFLR2 GG : Nodes, Faces = 29895 57546 AFLR2 GG : Nodes, Faces = 29897 57550 AFLR2 : CPU Time = 0.090 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 29897 57550 AFLR2 : CPU Time = 0.010 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 29897 Number of elements = 59794 Number of tris = 57550 Number of quad = 0 Getting 2D mesh for body 1 (of 1) AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 2224 0 AFLR2 : CPU Time = 0.001 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 2224 2224 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 446 894 AFLR2 IG : Nodes, Faces = 892 1786 AFLR2 IG : Nodes, Faces = 918 1838 AFLR2 IG : Nodes, Faces = 1033 2068 AFLR2 IG : Nodes, Faces = 1133 2268 AFLR2 IG : Nodes, Faces = 1233 2468 AFLR2 IG : Nodes, Faces = 1333 2668 AFLR2 IG : Nodes, Faces = 1338 2678 AFLR2 IG : Nodes, Faces = 1433 2868 AFLR2 IG : Nodes, Faces = 1533 3068 AFLR2 IG : Nodes, Faces = 1633 3268 AFLR2 IG : Nodes, Faces = 1733 3468 AFLR2 IG : Nodes, Faces = 1784 3570 AFLR2 IG : Nodes, Faces = 1833 3668 AFLR2 IG : Nodes, Faces = 1858 3718 AFLR2 IG : Nodes, Faces = 2224 4450 AFLR2 IG : Nodes, Faces = 2228 4450 AFLR2 IG : Nodes, Faces = 2224 2224 AFLR2 : CPU Time = 0.049 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 2224 2224 AFLR2 GG : Nodes, Faces = 4122 6020 AFLR2 GG : Nodes, Faces = 5812 9400 AFLR2 GG : Nodes, Faces = 7299 12374 AFLR2 GG : Nodes, Faces = 8574 14924 AFLR2 GG : Nodes, Faces = 9729 17234 AFLR2 GG : Nodes, Faces = 10787 19350 AFLR2 GG : Nodes, Faces = 11767 21310 AFLR2 GG : Nodes, Faces = 12683 23142 AFLR2 GG : Nodes, Faces = 13516 24808 AFLR2 GG : Nodes, Faces = 14278 26332 AFLR2 GG : Nodes, Faces = 14999 27774 AFLR2 GG : Nodes, Faces = 15682 29140 AFLR2 GG : Nodes, Faces = 16312 30400 AFLR2 GG : Nodes, Faces = 16899 31574 AFLR2 GG : Nodes, Faces = 17451 32678 AFLR2 GG : Nodes, Faces = 17959 33694 AFLR2 GG : Nodes, Faces = 18443 34662 AFLR2 GG : Nodes, Faces = 18877 35530 AFLR2 GG : Nodes, Faces = 19283 36342 AFLR2 GG : Nodes, Faces = 19650 37076 AFLR2 GG : Nodes, Faces = 19994 37764 AFLR2 GG : Nodes, Faces = 20325 38426 AFLR2 GG : Nodes, Faces = 20638 39052 AFLR2 GG : Nodes, Faces = 20940 39656 AFLR2 GG : Nodes, Faces = 21240 40256 AFLR2 GG : Nodes, Faces = 21523 40822 AFLR2 GG : Nodes, Faces = 21792 41360 AFLR2 GG : Nodes, Faces = 22053 41882 AFLR2 GG : Nodes, Faces = 22305 42386 AFLR2 GG : Nodes, Faces = 22521 42818 AFLR2 GG : Nodes, Faces = 22696 43168 AFLR2 GG : Nodes, Faces = 22829 43434 AFLR2 GG : Nodes, Faces = 22953 43682 AFLR2 GG : Nodes, Faces = 23050 43876 AFLR2 GG : Nodes, Faces = 23110 43996 AFLR2 GG : Nodes, Faces = 23139 44054 AFLR2 GG : Nodes, Faces = 23157 44090 AFLR2 GG : Nodes, Faces = 23175 44126 AFLR2 GG : Nodes, Faces = 23183 44142 AFLR2 GG : Nodes, Faces = 23187 44150 AFLR2 : CPU Time = 0.147 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 23187 44150 AFLR2 : CPU Time = 0.009 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 23187 Number of elements = 46374 Number of tris = 44150 Number of quad = 0 EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 2244 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 2244 2244 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 450 902 AFLR2 IG : Nodes, Faces = 900 1802 AFLR2 IG : Nodes, Faces = 1145 2292 AFLR2 IG : Nodes, Faces = 1260 2522 AFLR2 IG : Nodes, Faces = 1350 2702 AFLR2 IG : Nodes, Faces = 1360 2722 AFLR2 IG : Nodes, Faces = 1460 2922 AFLR2 IG : Nodes, Faces = 1560 3122 AFLR2 IG : Nodes, Faces = 1660 3322 AFLR2 IG : Nodes, Faces = 1760 3522 AFLR2 IG : Nodes, Faces = 1800 3602 AFLR2 IG : Nodes, Faces = 1860 3722 AFLR2 IG : Nodes, Faces = 1960 3922 AFLR2 IG : Nodes, Faces = 2060 4122 AFLR2 IG : Nodes, Faces = 2085 4172 AFLR2 IG : Nodes, Faces = 2244 4490 AFLR2 IG : Nodes, Faces = 2248 4490 AFLR2 IG : Nodes, Faces = 2244 2244 AFLR2 : CPU Time = 0.033 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 2244 2244 AFLR2 GG : Nodes, Faces = 4283 6322 AFLR2 GG : Nodes, Faces = 6128 10012 AFLR2 GG : Nodes, Faces = 7863 13482 AFLR2 GG : Nodes, Faces = 9464 16684 AFLR2 GG : Nodes, Faces = 10948 19652 AFLR2 GG : Nodes, Faces = 12322 22400 AFLR2 GG : Nodes, Faces = 13619 24994 AFLR2 GG : Nodes, Faces = 14829 27414 AFLR2 GG : Nodes, Faces = 15981 29718 AFLR2 GG : Nodes, Faces = 17082 31920 AFLR2 GG : Nodes, Faces = 18110 33976 AFLR2 GG : Nodes, Faces = 19081 35918 AFLR2 GG : Nodes, Faces = 20014 37784 AFLR2 GG : Nodes, Faces = 20924 39604 AFLR2 GG : Nodes, Faces = 21782 41320 AFLR2 GG : Nodes, Faces = 22595 42946 AFLR2 GG : Nodes, Faces = 23377 44510 AFLR2 GG : Nodes, Faces = 24129 46014 AFLR2 GG : Nodes, Faces = 24840 47436 AFLR2 GG : Nodes, Faces = 25522 48800 AFLR2 GG : Nodes, Faces = 26170 50096 AFLR2 GG : Nodes, Faces = 26793 51342 AFLR2 GG : Nodes, Faces = 27346 52448 AFLR2 GG : Nodes, Faces = 27846 53448 AFLR2 GG : Nodes, Faces = 28280 54316 AFLR2 GG : Nodes, Faces = 28652 55060 AFLR2 GG : Nodes, Faces = 28920 55596 AFLR2 GG : Nodes, Faces = 29143 56042 AFLR2 GG : Nodes, Faces = 29358 56472 AFLR2 GG : Nodes, Faces = 29550 56856 AFLR2 GG : Nodes, Faces = 29693 57142 AFLR2 GG : Nodes, Faces = 29805 57366 AFLR2 GG : Nodes, Faces = 29875 57506 AFLR2 GG : Nodes, Faces = 29895 57546 AFLR2 GG : Nodes, Faces = 29897 57550 AFLR2 : CPU Time = 0.138 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 29897 57550 AFLR2 : CPU Time = 0.013 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 29897 Number of elements = 59794 Number of tris = 57550 Number of quad = 0 CAPS Info: Hit last success -- going live! Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 CAPS Info: Hit last success -- going live! Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 2224 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 2224 2224 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 446 894 AFLR2 IG : Nodes, Faces = 892 1786 AFLR2 IG : Nodes, Faces = 918 1838 AFLR2 IG : Nodes, Faces = 1033 2068 AFLR2 IG : Nodes, Faces = 1133 2268 AFLR2 IG : Nodes, Faces = 1233 2468 AFLR2 IG : Nodes, Faces = 1333 2668 AFLR2 IG : Nodes, Faces = 1338 2678 AFLR2 IG : Nodes, Faces = 1433 2868 AFLR2 IG : Nodes, Faces = 1533 3068 AFLR2 IG : Nodes, Faces = 1633 3268 AFLR2 IG : Nodes, Faces = 1733 3468 AFLR2 IG : Nodes, Faces = 1784 3570 AFLR2 IG : Nodes, Faces = 1833 3668 AFLR2 IG : Nodes, Faces = 1858 3718 AFLR2 IG : Nodes, Faces = 2224 4450 AFLR2 IG : Nodes, Faces = 2228 4450 AFLR2 IG : Nodes, Faces = 2224 2224 AFLR2 : CPU Time = 0.030 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 2224 2224 AFLR2 GG : Nodes, Faces = 4122 6020 AFLR2 GG : Nodes, Faces = 5812 9400 AFLR2 GG : Nodes, Faces = 7299 12374 AFLR2 GG : Nodes, Faces = 8574 14924 AFLR2 GG : Nodes, Faces = 9729 17234 AFLR2 GG : Nodes, Faces = 10787 19350 AFLR2 GG : Nodes, Faces = 11767 21310 AFLR2 GG : Nodes, Faces = 12683 23142 AFLR2 GG : Nodes, Faces = 13516 24808 AFLR2 GG : Nodes, Faces = 14278 26332 AFLR2 GG : Nodes, Faces = 14999 27774 AFLR2 GG : Nodes, Faces = 15682 29140 AFLR2 GG : Nodes, Faces = 16312 30400 AFLR2 GG : Nodes, Faces = 16899 31574 AFLR2 GG : Nodes, Faces = 17451 32678 AFLR2 GG : Nodes, Faces = 17959 33694 AFLR2 GG : Nodes, Faces = 18443 34662 AFLR2 GG : Nodes, Faces = 18877 35530 AFLR2 GG : Nodes, Faces = 19283 36342 AFLR2 GG : Nodes, Faces = 19650 37076 AFLR2 GG : Nodes, Faces = 19994 37764 AFLR2 GG : Nodes, Faces = 20325 38426 AFLR2 GG : Nodes, Faces = 20638 39052 AFLR2 GG : Nodes, Faces = 20940 39656 AFLR2 GG : Nodes, Faces = 21240 40256 AFLR2 GG : Nodes, Faces = 21523 40822 AFLR2 GG : Nodes, Faces = 21792 41360 AFLR2 GG : Nodes, Faces = 22053 41882 AFLR2 GG : Nodes, Faces = 22305 42386 AFLR2 GG : Nodes, Faces = 22521 42818 AFLR2 GG : Nodes, Faces = 22696 43168 AFLR2 GG : Nodes, Faces = 22829 43434 AFLR2 GG : Nodes, Faces = 22953 43682 AFLR2 GG : Nodes, Faces = 23050 43876 AFLR2 GG : Nodes, Faces = 23110 43996 AFLR2 GG : Nodes, Faces = 23139 44054 AFLR2 GG : Nodes, Faces = 23157 44090 AFLR2 GG : Nodes, Faces = 23175 44126 AFLR2 GG : Nodes, Faces = 23183 44142 AFLR2 GG : Nodes, Faces = 23187 44150 AFLR2 : CPU Time = 0.091 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 23187 44150 AFLR2 : CPU Time = 0.009 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 23187 Number of elements = 46374 Number of tris = 44150 Number of quad = 0 CAPS Info: Hit last success -- going live! Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 ok test_phase (test_aflr2.TestAFLR2.test_phase) ... Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 2244 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 2244 2244 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 450 902 AFLR2 IG : Nodes, Faces = 900 1802 AFLR2 IG : Nodes, Faces = 1145 2292 AFLR2 IG : Nodes, Faces = 1260 2522 AFLR2 IG : Nodes, Faces = 1350 2702 AFLR2 IG : Nodes, Faces = 1360 2722 AFLR2 IG : Nodes, Faces = 1460 2922 AFLR2 IG : Nodes, Faces = 1560 3122 AFLR2 IG : Nodes, Faces = 1660 3322 AFLR2 IG : Nodes, Faces = 1760 3522 AFLR2 IG : Nodes, Faces = 1800 3602 AFLR2 IG : Nodes, Faces = 1860 3722 AFLR2 IG : Nodes, Faces = 1960 3922 AFLR2 IG : Nodes, Faces = 2060 4122 AFLR2 IG : Nodes, Faces = 2085 4172 AFLR2 IG : Nodes, Faces = 2244 4490 AFLR2 IG : Nodes, Faces = 2248 4490 AFLR2 IG : Nodes, Faces = 2244 2244 AFLR2 : CPU Time = 0.032 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 2244 2244 AFLR2 GG : Nodes, Faces = 4283 6322 AFLR2 GG : Nodes, Faces = 6128 10012 AFLR2 GG : Nodes, Faces = 7863 13482 AFLR2 GG : Nodes, Faces = 9464 16684 AFLR2 GG : Nodes, Faces = 10948 19652 AFLR2 GG : Nodes, Faces = 12322 22400 AFLR2 GG : Nodes, Faces = 13619 24994 AFLR2 GG : Nodes, Faces = 14829 27414 AFLR2 GG : Nodes, Faces = 15981 29718 AFLR2 GG : Nodes, Faces = 17082 31920 AFLR2 GG : Nodes, Faces = 18110 33976 AFLR2 GG : Nodes, Faces = 19081 35918 AFLR2 GG : Nodes, Faces = 20014 37784 AFLR2 GG : Nodes, Faces = 20924 39604 AFLR2 GG : Nodes, Faces = 21782 41320 AFLR2 GG : Nodes, Faces = 22595 42946 AFLR2 GG : Nodes, Faces = 23377 44510 AFLR2 GG : Nodes, Faces = 24129 46014 AFLR2 GG : Nodes, Faces = 24840 47436 AFLR2 GG : Nodes, Faces = 25522 48800 AFLR2 GG : Nodes, Faces = 26170 50096 AFLR2 GG : Nodes, Faces = 26793 51342 AFLR2 GG : Nodes, Faces = 27346 52448 AFLR2 GG : Nodes, Faces = 27846 53448 AFLR2 GG : Nodes, Faces = 28280 54316 AFLR2 GG : Nodes, Faces = 28652 55060 AFLR2 GG : Nodes, Faces = 28920 55596 AFLR2 GG : Nodes, Faces = 29143 56042 AFLR2 GG : Nodes, Faces = 29358 56472 AFLR2 GG : Nodes, Faces = 29550 56856 AFLR2 GG : Nodes, Faces = 29693 57142 AFLR2 GG : Nodes, Faces = 29805 57366 AFLR2 GG : Nodes, Faces = 29875 57506 AFLR2 GG : Nodes, Faces = 29895 57546 AFLR2 GG : Nodes, Faces = 29897 57550 AFLR2 : CPU Time = 0.086 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 29897 57550 AFLR2 : CPU Time = 0.008 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 29897 Number of elements = 59794 Number of tris = 57550 Number of quad = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 48 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 48 48 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 10 22 AFLR2 IG : Nodes, Faces = 20 42 AFLR2 IG : Nodes, Faces = 30 62 AFLR2 IG : Nodes, Faces = 40 82 AFLR2 IG : Nodes, Faces = 45 92 AFLR2 IG : Nodes, Faces = 46 94 AFLR2 IG : Nodes, Faces = 48 98 AFLR2 IG : Nodes, Faces = 52 98 AFLR2 IG : Nodes, Faces = 48 48 AFLR2 : CPU Time = 0.001 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 48 48 AFLR2 GG : Nodes, Faces = 88 128 AFLR2 GG : Nodes, Faces = 109 170 AFLR2 GG : Nodes, Faces = 124 200 AFLR2 GG : Nodes, Faces = 136 224 AFLR2 GG : Nodes, Faces = 148 248 AFLR2 GG : Nodes, Faces = 161 274 AFLR2 GG : Nodes, Faces = 171 294 AFLR2 GG : Nodes, Faces = 181 314 AFLR2 GG : Nodes, Faces = 187 326 AFLR2 GG : Nodes, Faces = 190 332 AFLR2 : CPU Time = 0.001 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 190 332 AFLR2 : CPU Time = 0.000 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 190 Number of elements = 380 Number of tris = 332 Number of quad = 0 ok test_reenter (test_aflr2.TestAFLR2.test_reenter) ... Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 344 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 344 344 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 70 142 AFLR2 IG : Nodes, Faces = 140 282 AFLR2 IG : Nodes, Faces = 210 422 AFLR2 IG : Nodes, Faces = 280 562 AFLR2 IG : Nodes, Faces = 339 680 AFLR2 IG : Nodes, Faces = 340 682 AFLR2 IG : Nodes, Faces = 344 690 AFLR2 IG : Nodes, Faces = 348 690 AFLR2 IG : Nodes, Faces = 344 344 AFLR2 : CPU Time = 0.001 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 344 344 AFLR2 GG : Nodes, Faces = 679 1014 AFLR2 GG : Nodes, Faces = 1006 1668 AFLR2 GG : Nodes, Faces = 1321 2298 AFLR2 GG : Nodes, Faces = 1604 2864 AFLR2 GG : Nodes, Faces = 1886 3428 AFLR2 GG : Nodes, Faces = 2155 3966 AFLR2 GG : Nodes, Faces = 2409 4474 AFLR2 GG : Nodes, Faces = 2649 4954 AFLR2 GG : Nodes, Faces = 2867 5390 AFLR2 GG : Nodes, Faces = 3063 5782 AFLR2 GG : Nodes, Faces = 3243 6142 AFLR2 GG : Nodes, Faces = 3400 6456 AFLR2 GG : Nodes, Faces = 3540 6736 AFLR2 GG : Nodes, Faces = 3665 6986 AFLR2 GG : Nodes, Faces = 3786 7228 AFLR2 GG : Nodes, Faces = 3900 7456 AFLR2 GG : Nodes, Faces = 4010 7676 AFLR2 GG : Nodes, Faces = 4114 7884 AFLR2 GG : Nodes, Faces = 4209 8074 AFLR2 GG : Nodes, Faces = 4292 8240 AFLR2 GG : Nodes, Faces = 4368 8392 AFLR2 GG : Nodes, Faces = 4439 8534 AFLR2 GG : Nodes, Faces = 4503 8662 AFLR2 GG : Nodes, Faces = 4560 8776 AFLR2 GG : Nodes, Faces = 4611 8878 AFLR2 GG : Nodes, Faces = 4650 8956 AFLR2 GG : Nodes, Faces = 4677 9010 AFLR2 GG : Nodes, Faces = 4695 9046 AFLR2 GG : Nodes, Faces = 4705 9066 AFLR2 : CPU Time = 0.009 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 4705 9066 AFLR2 : CPU Time = 0.001 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 4705 Number of elements = 9410 Number of tris = 9066 Number of quad = 0 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file libMeshb expects 2D meshes in the x-y plane... attempting to rotate mesh!Swapping z and y coordinates! Writing FAST file .... Finished writing FAST file Writing SU2 file .... SU2 expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 344 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 344 344 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 70 142 AFLR2 IG : Nodes, Faces = 140 282 AFLR2 IG : Nodes, Faces = 210 422 AFLR2 IG : Nodes, Faces = 280 562 AFLR2 IG : Nodes, Faces = 339 680 AFLR2 IG : Nodes, Faces = 340 682 AFLR2 IG : Nodes, Faces = 344 690 AFLR2 IG : Nodes, Faces = 348 690 AFLR2 IG : Nodes, Faces = 344 344 AFLR2 : CPU Time = 0.001 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GGp: Nodes, Faces = 344 344 AFLR2 GGp: Nodes, Faces = 682 1020 AFLR2 GGp: Nodes, Faces = 1010 1676 AFLR2 GGp: Nodes, Faces = 1316 2288 AFLR2 GGp: Nodes, Faces = 1592 2840 AFLR2 GGp: Nodes, Faces = 1855 3366 AFLR2 GGp: Nodes, Faces = 2106 3868 AFLR2 GGp: Nodes, Faces = 2341 4338 AFLR2 GGp: Nodes, Faces = 2551 4758 AFLR2 GGp: Nodes, Faces = 2741 5138 AFLR2 GGp: Nodes, Faces = 2917 5490 AFLR2 GGp: Nodes, Faces = 3082 5820 AFLR2 GGp: Nodes, Faces = 3240 6136 AFLR2 GGp: Nodes, Faces = 3379 6414 AFLR2 GGp: Nodes, Faces = 3513 6682 AFLR2 GGp: Nodes, Faces = 3642 6940 AFLR2 GGp: Nodes, Faces = 3748 7152 AFLR2 GGp: Nodes, Faces = 3846 7348 AFLR2 GGp: Nodes, Faces = 3931 7518 AFLR2 GGp: Nodes, Faces = 3999 7654 AFLR2 GGp: Nodes, Faces = 4044 7744 AFLR2 GGp: Nodes, Faces = 4058 7772 AFLR2 : CPU Time = 0.059 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 4058 7772 AFLR2 QI : Nodes, Faces = 4057 364 AFLR2 QI : Nodes, Faces = 4057 3703 AFLR2 QI : Nodes, Faces = 4057 7770 AFLR2 QI : Nodes, Faces = 4056 344 AFLR2 QI : Nodes, Faces = 4056 3712 AFLR2 QI : Nodes, Faces = 4056 7768 AFLR2 QI : Nodes, Faces = 4055 348 AFLR2 QI : Nodes, Faces = 4055 3709 AFLR2 QI : Nodes, Faces = 4055 7766 AFLR2 QI : Nodes, Faces = 4055 392 AFLR2 QI : Nodes, Faces = 4055 3687 AFLR2 QI : Nodes, Faces = 4055 7766 AFLR2 QI : Nodes, Faces = 4055 386 AFLR2 QI : Nodes, Faces = 4055 3690 AFLR2 QI : Nodes, Faces = 4055 386 AFLR2 QI : Nodes, Faces = 4055 3690 AFLR2 : CPU Time = 0.015 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 4055 Number of elements = 4420 Number of tris = 386 Number of quad = 3690 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file libMeshb expects 2D meshes in the x-y plane... attempting to rotate mesh!Swapping z and y coordinates! Writing SU2 file .... SU2 expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file ok test_setInput (test_aflr2.TestAFLR2.test_setInput) ... Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 344 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 344 344 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 70 142 AFLR2 IG : Nodes, Faces = 140 282 AFLR2 IG : Nodes, Faces = 210 422 AFLR2 IG : Nodes, Faces = 280 562 AFLR2 IG : Nodes, Faces = 339 680 AFLR2 IG : Nodes, Faces = 340 682 AFLR2 IG : Nodes, Faces = 344 690 AFLR2 IG : Nodes, Faces = 348 690 AFLR2 IG : Nodes, Faces = 344 344 AFLR2 : CPU Time = 0.001 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GGp: Nodes, Faces = 344 344 AFLR2 GGp: Nodes, Faces = 682 1020 AFLR2 GGp: Nodes, Faces = 1010 1676 AFLR2 GGp: Nodes, Faces = 1316 2288 AFLR2 GGp: Nodes, Faces = 1592 2840 AFLR2 GGp: Nodes, Faces = 1855 3366 AFLR2 GGp: Nodes, Faces = 2106 3868 AFLR2 GGp: Nodes, Faces = 2341 4338 AFLR2 GGp: Nodes, Faces = 2551 4758 AFLR2 GGp: Nodes, Faces = 2741 5138 AFLR2 GGp: Nodes, Faces = 2917 5490 AFLR2 GGp: Nodes, Faces = 3082 5820 AFLR2 GGp: Nodes, Faces = 3240 6136 AFLR2 GGp: Nodes, Faces = 3379 6414 AFLR2 GGp: Nodes, Faces = 3513 6682 AFLR2 GGp: Nodes, Faces = 3642 6940 AFLR2 GGp: Nodes, Faces = 3748 7152 AFLR2 GGp: Nodes, Faces = 3846 7348 AFLR2 GGp: Nodes, Faces = 3931 7518 AFLR2 GGp: Nodes, Faces = 3999 7654 AFLR2 GGp: Nodes, Faces = 4044 7744 AFLR2 GGp: Nodes, Faces = 4058 7772 AFLR2 : CPU Time = 0.045 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 4058 7772 AFLR2 QI : Nodes, Faces = 4057 364 AFLR2 QI : Nodes, Faces = 4057 3703 AFLR2 QI : Nodes, Faces = 4057 7770 AFLR2 QI : Nodes, Faces = 4056 344 AFLR2 QI : Nodes, Faces = 4056 3712 AFLR2 QI : Nodes, Faces = 4056 7768 AFLR2 QI : Nodes, Faces = 4055 348 AFLR2 QI : Nodes, Faces = 4055 3709 AFLR2 QI : Nodes, Faces = 4055 7766 AFLR2 QI : Nodes, Faces = 4055 392 AFLR2 QI : Nodes, Faces = 4055 3687 AFLR2 QI : Nodes, Faces = 4055 7766 AFLR2 QI : Nodes, Faces = 4055 386 AFLR2 QI : Nodes, Faces = 4055 3690 AFLR2 QI : Nodes, Faces = 4055 386 AFLR2 QI : Nodes, Faces = 4055 3690 AFLR2 : CPU Time = 0.012 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 4055 Number of elements = 4420 Number of tris = 386 Number of quad = 3690 Writing Tecplot file .... Finished writing Tecplot file ok test_Multiple_Mesh (test_aflr3.TestAFLR3.test_Multiple_Mesh) ... ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Getting volume mesh for body 1 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box, index = 1 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 7): Number of nodes = 1189 Number of elements = 6249 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4917 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = cylinder, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 7): Number of nodes = 6237 Number of elements = 34620 Number of triangles = 4438 Number of quadrilatarals = 0 Number of tetrahedrals = 30182 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = cone, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 7): Number of nodes = 13613 Number of elements = 76414 Number of triangles = 8142 Number of quadrilatarals = 0 Number of tetrahedrals = 68272 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 4 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = torus, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 4 (of 7): Number of nodes = 41618 Number of elements = 236483 Number of triangles = 19838 Number of quadrilatarals = 0 Number of tetrahedrals = 216645 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 5 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = sphere, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 5 (of 7): Number of nodes = 4369 Number of elements = 24223 Number of triangles = 3016 Number of quadrilatarals = 0 Number of tetrahedrals = 21207 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 6 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = boxhole, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 6 (of 7): Number of nodes = 11007 Number of elements = 60837 Number of triangles = 8632 Number of quadrilatarals = 0 Number of tetrahedrals = 52205 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 7 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = bullet, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 7 (of 7): Number of nodes = 10474 Number of elements = 58678 Number of triangles = 6352 Number of quadrilatarals = 0 Number of tetrahedrals = 52326 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Getting volume mesh for body 1 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 4 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 5 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 6 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 7 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 88507 Number of elements = 497504 Number of triangles = 51750 Number of quadrilatarals = 0 Number of tetrahedrals = 445754 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_all (test_aflr3.TestAFLR3.test_all) ... ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Name = farfield, index = 8 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Name = farfield, index = 8 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 17441 Number of elements = 99306 Number of triangles = 8306 Number of quadrilatarals = 0 Number of tetrahedrals = 91000 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_box (test_aflr3.TestAFLR3.test_box) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 2589 Number of elements = 13809 Number of triangles = 2758 Number of quadrilatarals = 0 Number of tetrahedrals = 11051 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_boxhole (test_aflr3.TestAFLR3.test_boxhole) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = boxhole, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = boxhole, index = 1 Name = farfield, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 3654 Number of elements = 19800 Number of triangles = 3394 Number of quadrilatarals = 0 Number of tetrahedrals = 16406 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_bullet (test_aflr3.TestAFLR3.test_bullet) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = bullet, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = bullet, index = 1 Name = farfield, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 5456 Number of elements = 30308 Number of triangles = 3656 Number of quadrilatarals = 0 Number of tetrahedrals = 26652 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_cone (test_aflr3.TestAFLR3.test_cone) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = cone, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = cone, index = 1 Name = farfield, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 4694 Number of elements = 25935 Number of triangles = 3326 Number of quadrilatarals = 0 Number of tetrahedrals = 22609 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_cylinder (test_aflr3.TestAFLR3.test_cylinder) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = cylinder, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = cylinder, index = 1 Name = farfield, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 5554 Number of elements = 30862 Number of triangles = 3756 Number of quadrilatarals = 0 Number of tetrahedrals = 27106 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_faceMatch (test_aflr3.TestAFLR3.test_faceMatch) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 2260 Number of elements = 12133 Number of triangles = 2222 Number of quadrilatarals = 0 Number of tetrahedrals = 9911 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 2) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 2) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 2392 Number of elements = 12577 Number of triangles = 2666 Number of quadrilatarals = 0 Number of tetrahedrals = 9911 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 2): Number of nodes = 1208 Number of elements = 6360 Number of triangles = 1334 Number of quadrilatarals = 0 Number of tetrahedrals = 5026 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 2): Number of nodes = 1184 Number of elements = 6217 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4885 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 3341 Number of elements = 18069 Number of triangles = 3110 Number of quadrilatarals = 0 Number of tetrahedrals = 14959 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 3606 Number of elements = 18961 Number of triangles = 4002 Number of quadrilatarals = 0 Number of tetrahedrals = 14959 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 3): Number of nodes = 1208 Number of elements = 6360 Number of triangles = 1334 Number of quadrilatarals = 0 Number of tetrahedrals = 5026 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 3): Number of nodes = 1184 Number of elements = 6217 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4885 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 3): Number of nodes = 1214 Number of elements = 6384 Number of triangles = 1336 Number of quadrilatarals = 0 Number of tetrahedrals = 5048 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 4414 Number of elements = 23974 Number of triangles = 3998 Number of quadrilatarals = 0 Number of tetrahedrals = 19976 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 4) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 4) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 4) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 4 (of 4) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 4811 Number of elements = 25310 Number of triangles = 5334 Number of quadrilatarals = 0 Number of tetrahedrals = 19976 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 4) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 4): Number of nodes = 1208 Number of elements = 6360 Number of triangles = 1334 Number of quadrilatarals = 0 Number of tetrahedrals = 5026 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 4) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 4): Number of nodes = 1184 Number of elements = 6217 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4885 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 4) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 4): Number of nodes = 1214 Number of elements = 6384 Number of triangles = 1336 Number of quadrilatarals = 0 Number of tetrahedrals = 5048 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 4 (of 4) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 4 (of 4): Number of nodes = 1205 Number of elements = 6349 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5017 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 5490 Number of elements = 29891 Number of triangles = 4886 Number of quadrilatarals = 0 Number of tetrahedrals = 25005 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 4 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 5 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 6019 Number of elements = 31671 Number of triangles = 6666 Number of quadrilatarals = 0 Number of tetrahedrals = 25005 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 5): Number of nodes = 1208 Number of elements = 6360 Number of triangles = 1334 Number of quadrilatarals = 0 Number of tetrahedrals = 5026 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 5): Number of nodes = 1184 Number of elements = 6217 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4885 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 5): Number of nodes = 1214 Number of elements = 6384 Number of triangles = 1336 Number of quadrilatarals = 0 Number of tetrahedrals = 5048 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 4 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 4 (of 5): Number of nodes = 1205 Number of elements = 6349 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5017 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 5 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 5 (of 5): Number of nodes = 1208 Number of elements = 6361 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5029 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 6542 Number of elements = 35667 Number of triangles = 5774 Number of quadrilatarals = 0 Number of tetrahedrals = 29893 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 6) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 6) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 6) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 4 (of 6) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 5 (of 6) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 6 (of 6) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 7203 Number of elements = 37891 Number of triangles = 7998 Number of quadrilatarals = 0 Number of tetrahedrals = 29893 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 6) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 6): Number of nodes = 1208 Number of elements = 6360 Number of triangles = 1334 Number of quadrilatarals = 0 Number of tetrahedrals = 5026 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 6) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 6): Number of nodes = 1184 Number of elements = 6217 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4885 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 6) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 6): Number of nodes = 1214 Number of elements = 6384 Number of triangles = 1336 Number of quadrilatarals = 0 Number of tetrahedrals = 5048 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 4 (of 6) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 4 (of 6): Number of nodes = 1205 Number of elements = 6349 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5017 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 5 (of 6) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 5 (of 6): Number of nodes = 1208 Number of elements = 6361 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5029 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 6 (of 6) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 6 (of 6): Number of nodes = 1184 Number of elements = 6220 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4888 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 7601 Number of elements = 41489 Number of triangles = 6662 Number of quadrilatarals = 0 Number of tetrahedrals = 34827 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 4 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 5 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 6 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 7 (of 7) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 8394 Number of elements = 44157 Number of triangles = 9330 Number of quadrilatarals = 0 Number of tetrahedrals = 34827 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 7): Number of nodes = 1208 Number of elements = 6360 Number of triangles = 1334 Number of quadrilatarals = 0 Number of tetrahedrals = 5026 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 7): Number of nodes = 1184 Number of elements = 6217 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4885 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 7): Number of nodes = 1214 Number of elements = 6384 Number of triangles = 1336 Number of quadrilatarals = 0 Number of tetrahedrals = 5048 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 4 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 4 (of 7): Number of nodes = 1205 Number of elements = 6349 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5017 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 5 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 5 (of 7): Number of nodes = 1208 Number of elements = 6361 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5029 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 6 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 6 (of 7): Number of nodes = 1184 Number of elements = 6220 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4888 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 7 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 7 (of 7): Number of nodes = 1191 Number of elements = 6266 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4934 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 19800 Number of elements = 109798 Number of triangles = 15540 Number of quadrilatarals = 0 Number of tetrahedrals = 94258 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 4 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 5 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 6 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 7 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 8 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 9 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 10 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 11 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 12 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 13 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 14 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 15 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 16 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 17 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 18 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 19 (of 19) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 22741 Number of elements = 119570 Number of triangles = 25312 Number of quadrilatarals = 0 Number of tetrahedrals = 94258 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 19): Number of nodes = 1208 Number of elements = 6360 Number of triangles = 1334 Number of quadrilatarals = 0 Number of tetrahedrals = 5026 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 19): Number of nodes = 1184 Number of elements = 6217 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4885 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 19): Number of nodes = 1214 Number of elements = 6384 Number of triangles = 1336 Number of quadrilatarals = 0 Number of tetrahedrals = 5048 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 4 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 4 (of 19): Number of nodes = 1205 Number of elements = 6349 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5017 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 5 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 5 (of 19): Number of nodes = 1208 Number of elements = 6361 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5029 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 6 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 6 (of 19): Number of nodes = 1184 Number of elements = 6220 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4888 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 7 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 7 (of 19): Number of nodes = 1191 Number of elements = 6266 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4934 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 8 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 8 (of 19): Number of nodes = 1193 Number of elements = 6272 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4940 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 9 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 9 (of 19): Number of nodes = 1176 Number of elements = 6165 Number of triangles = 1330 Number of quadrilatarals = 0 Number of tetrahedrals = 4835 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 10 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 10 (of 19): Number of nodes = 1203 Number of elements = 6314 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4982 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 11 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 11 (of 19): Number of nodes = 1192 Number of elements = 6269 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4937 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 12 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 12 (of 19): Number of nodes = 1192 Number of elements = 6269 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4937 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 13 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 13 (of 19): Number of nodes = 1198 Number of elements = 6296 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4964 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 14 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 14 (of 19): Number of nodes = 1223 Number of elements = 6443 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 5111 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 15 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 15 (of 19): Number of nodes = 1184 Number of elements = 6224 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4892 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 16 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 16 (of 19): Number of nodes = 1195 Number of elements = 6287 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4955 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 17 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 17 (of 19): Number of nodes = 1197 Number of elements = 6311 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4979 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 18 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 18 (of 19): Number of nodes = 1203 Number of elements = 6310 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4978 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 19 (of 19) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 19 (of 19): Number of nodes = 1191 Number of elements = 6253 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4921 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ok test_faceMatch_MultiDomain (test_aflr3.TestAFLR3.test_faceMatch_MultiDomain) ... ../csmData/MultiDomain/example1.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 8857 Number of elements = 49191 Number of triangles = 6284 Number of quadrilatarals = 0 Number of tetrahedrals = 42907 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 2) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 2) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 8989 Number of elements = 49635 Number of triangles = 6728 Number of quadrilatarals = 0 Number of tetrahedrals = 42907 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 2): Number of nodes = 7796 Number of elements = 43368 Number of triangles = 5396 Number of quadrilatarals = 0 Number of tetrahedrals = 37972 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 2): Number of nodes = 1193 Number of elements = 6267 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4935 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example2.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 9944 Number of elements = 55193 Number of triangles = 7174 Number of quadrilatarals = 0 Number of tetrahedrals = 48019 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 10218 Number of elements = 56081 Number of triangles = 8062 Number of quadrilatarals = 0 Number of tetrahedrals = 48019 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 3): Number of nodes = 7818 Number of elements = 43469 Number of triangles = 5398 Number of quadrilatarals = 0 Number of tetrahedrals = 38071 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 3): Number of nodes = 1202 Number of elements = 6320 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4988 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 3): Number of nodes = 1198 Number of elements = 6292 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4960 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example3.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 9609 Number of elements = 53228 Number of triangles = 6994 Number of quadrilatarals = 0 Number of tetrahedrals = 46234 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 9829 Number of elements = 53956 Number of triangles = 7722 Number of quadrilatarals = 0 Number of tetrahedrals = 46234 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 3): Number of nodes = 7789 Number of elements = 43295 Number of triangles = 5394 Number of quadrilatarals = 0 Number of tetrahedrals = 37901 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 3): Number of nodes = 1186 Number of elements = 6230 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4898 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 3): Number of nodes = 854 Number of elements = 4431 Number of triangles = 996 Number of quadrilatarals = 0 Number of tetrahedrals = 3435 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example4.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 9348 Number of elements = 51734 Number of triangles = 6812 Number of quadrilatarals = 0 Number of tetrahedrals = 44922 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 9531 Number of elements = 52330 Number of triangles = 7408 Number of quadrilatarals = 0 Number of tetrahedrals = 44922 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 3): Number of nodes = 7804 Number of elements = 43358 Number of triangles = 5386 Number of quadrilatarals = 0 Number of tetrahedrals = 37972 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 3): Number of nodes = 1200 Number of elements = 6311 Number of triangles = 1332 Number of quadrilatarals = 0 Number of tetrahedrals = 4979 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 3): Number of nodes = 527 Number of elements = 2661 Number of triangles = 690 Number of quadrilatarals = 0 Number of tetrahedrals = 1971 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example6.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 9183 Number of elements = 50871 Number of triangles = 6632 Number of quadrilatarals = 0 Number of tetrahedrals = 44239 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 9322 Number of elements = 51307 Number of triangles = 7068 Number of quadrilatarals = 0 Number of tetrahedrals = 44239 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 3): Number of nodes = 7927 Number of elements = 44116 Number of triangles = 5382 Number of quadrilatarals = 0 Number of tetrahedrals = 38734 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 3): Number of nodes = 868 Number of elements = 4530 Number of triangles = 996 Number of quadrilatarals = 0 Number of tetrahedrals = 3534 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 3): Number of nodes = 527 Number of elements = 2661 Number of triangles = 690 Number of quadrilatarals = 0 Number of tetrahedrals = 1971 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example7.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 10181 Number of elements = 56797 Number of triangles = 6782 Number of quadrilatarals = 0 Number of tetrahedrals = 50015 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 10671 Number of elements = 58561 Number of triangles = 8546 Number of quadrilatarals = 0 Number of tetrahedrals = 50015 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 3): Number of nodes = 7741 Number of elements = 43010 Number of triangles = 5362 Number of quadrilatarals = 0 Number of tetrahedrals = 37648 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 3): Number of nodes = 2692 Number of elements = 14435 Number of triangles = 2800 Number of quadrilatarals = 0 Number of tetrahedrals = 11635 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 3): Number of nodes = 238 Number of elements = 1116 Number of triangles = 384 Number of quadrilatarals = 0 Number of tetrahedrals = 732 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example8.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 1494 Number of elements = 7708 Number of triangles = 1988 Number of quadrilatarals = 0 Number of tetrahedrals = 5720 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 3) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 1558 Number of elements = 7832 Number of triangles = 2112 Number of quadrilatarals = 0 Number of tetrahedrals = 5720 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 3): Number of nodes = 1151 Number of elements = 6028 Number of triangles = 1308 Number of quadrilatarals = 0 Number of tetrahedrals = 4720 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 3): Number of nodes = 363 Number of elements = 1645 Number of triangles = 720 Number of quadrilatarals = 0 Number of tetrahedrals = 925 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 3): Number of nodes = 44 Number of elements = 159 Number of triangles = 84 Number of quadrilatarals = 0 Number of tetrahedrals = 75 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example9.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 5075 Number of elements = 27761 Number of triangles = 4072 Number of quadrilatarals = 0 Number of tetrahedrals = 23689 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 2) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 2) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 5221 Number of elements = 28313 Number of triangles = 4624 Number of quadrilatarals = 0 Number of tetrahedrals = 23689 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 2): Number of nodes = 4882 Number of elements = 26790 Number of triangles = 4040 Number of quadrilatarals = 0 Number of tetrahedrals = 22750 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 2): Number of nodes = 339 Number of elements = 1523 Number of triangles = 584 Number of quadrilatarals = 0 Number of tetrahedrals = 939 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/multi_prim.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 32776 Number of elements = 189806 Number of triangles = 8496 Number of quadrilatarals = 0 Number of tetrahedrals = 181310 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 3 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 4 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 5 (of 5) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 36115 Number of elements = 203130 Number of triangles = 21820 Number of quadrilatarals = 0 Number of tetrahedrals = 181310 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 5): Number of nodes = 28584 Number of elements = 162362 Number of triangles = 15158 Number of quadrilatarals = 0 Number of tetrahedrals = 147204 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 5): Number of nodes = 1425 Number of elements = 7592 Number of triangles = 1456 Number of quadrilatarals = 0 Number of tetrahedrals = 6136 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 3 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 3 (of 5): Number of nodes = 4138 Number of elements = 22901 Number of triangles = 2938 Number of quadrilatarals = 0 Number of tetrahedrals = 19963 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 4 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 4 (of 5): Number of nodes = 711 Number of elements = 3685 Number of triangles = 844 Number of quadrilatarals = 0 Number of tetrahedrals = 2841 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 5 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 5 (of 5): Number of nodes = 1257 Number of elements = 6590 Number of triangles = 1424 Number of quadrilatarals = 0 Number of tetrahedrals = 5166 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/cyl_seam.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 16639 Number of elements = 94369 Number of triangles = 8800 Number of quadrilatarals = 0 Number of tetrahedrals = 85569 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 2) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Getting volume mesh for body 2 (of 2) EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 18563 Number of elements = 101745 Number of triangles = 16176 Number of quadrilatarals = 0 Number of tetrahedrals = 85569 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting volume mesh for body 1 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 1 (of 2): Number of nodes = 12009 Number of elements = 67436 Number of triangles = 7140 Number of quadrilatarals = 0 Number of tetrahedrals = 60296 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh for body 2 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh for body 2 (of 2): Number of nodes = 6554 Number of elements = 34309 Number of triangles = 9036 Number of quadrilatarals = 0 Number of tetrahedrals = 25273 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ok test_journal (test_aflr3.TestAFLR3.test_journal) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 20671 Number of elements = 119572 Number of triangles = 5446 Number of quadrilatarals = 0 Number of tetrahedrals = 114126 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 18912 Number of elements = 109307 Number of triangles = 5256 Number of quadrilatarals = 0 Number of tetrahedrals = 104051 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 20671 Number of elements = 119572 Number of triangles = 5446 Number of quadrilatarals = 0 Number of tetrahedrals = 114126 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 18912 Number of elements = 109307 Number of triangles = 5256 Number of quadrilatarals = 0 Number of tetrahedrals = 104051 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 ok test_phase (test_aflr3.TestAFLR3.test_phase) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 20671 Number of elements = 119572 Number of triangles = 5446 Number of quadrilatarals = 0 Number of tetrahedrals = 114126 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 18912 Number of elements = 109307 Number of triangles = 5256 Number of quadrilatarals = 0 Number of tetrahedrals = 104051 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_quad (test_aflr3.TestAFLR3.test_quad) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 28583 Number of elements = 129179 Number of triangles = 410 Number of quadrilatarals = 3218 Number of tetrahedrals = 118367 Number of pyramids = 0 Number of prisms = 748 Number of hexahedrals = 6436 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file ok test_reenter (test_aflr3.TestAFLR3.test_reenter) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 21315 Number of elements = 123546 Number of triangles = 5542 Number of quadrilatarals = 0 Number of tetrahedrals = 118004 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 20272 Number of elements = 117350 Number of triangles = 5384 Number of quadrilatarals = 0 Number of tetrahedrals = 111966 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file ok test_setInput (test_aflr3.TestAFLR3.test_setInput) ... EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! ok test_sphere (test_aflr3.TestAFLR3.test_sphere) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = sphere, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = sphere, index = 1 Name = farfield, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 4989 Number of elements = 27641 Number of triangles = 3462 Number of quadrilatarals = 0 Number of tetrahedrals = 24179 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_torus (test_aflr3.TestAFLR3.test_torus) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = torus, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = torus, index = 1 Name = farfield, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 6401 Number of elements = 35742 Number of triangles = 4048 Number of quadrilatarals = 0 Number of tetrahedrals = 31694 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok test_transp (test_aflr3.TestAFLR3.test_transp) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Getting mesh sizing parameters Mesh sizing name - Wake Done getting mesh sizing parameters Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 41690 Number of elements = 240892 Number of triangles = 11826 Number of quadrilatarals = 0 Number of tetrahedrals = 229066 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Getting mesh sizing parameters Mesh sizing name - Wake Done getting mesh sizing parameters Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 45515 Number of elements = 263531 Number of triangles = 11696 Number of quadrilatarals = 0 Number of tetrahedrals = 251835 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Getting mesh sizing parameters Mesh sizing name - Wake Done getting mesh sizing parameters Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 41690 Number of elements = 240762 Number of triangles = 11696 Number of quadrilatarals = 0 Number of tetrahedrals = 229066 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file ok Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 test_Edge_scaleFactor (test_aflr4.TestAFLR4.test_Edge_scaleFactor) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - trailingEdge Done getting mesh sizing parameters ok test_Face_scaleFactor (test_aflr4.TestAFLR4.test_Face_scaleFactor) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - leftWing Done getting mesh sizing parameters ok test_all (test_aflr4.TestAFLR4.test_all) ... ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Name = farfield, index = 8 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ok test_box (test_aflr4.TestAFLR4.test_box) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ok test_boxhole (test_aflr4.TestAFLR4.test_boxhole) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = boxhole, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_bullet (test_aflr4.TestAFLR4.test_bullet) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = bullet, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_cone (test_aflr4.TestAFLR4.test_cone) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = cone, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_cylinder (test_aflr4.TestAFLR4.test_cylinder) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = cylinder, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_erw (test_aflr4.TestAFLR4.test_erw) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - leftWing Done getting mesh sizing parameters ok test_faceMatch (test_aflr4.TestAFLR4.test_faceMatch) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wall, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_faceMatch_MultiDomain (test_aflr4.TestAFLR4.test_faceMatch_MultiDomain) ... ../csmData/MultiDomain/example1.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example2.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example3.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example4.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example6.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example7.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example8.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/example9.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/multi_prim.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ../csmData/MultiDomain/cyl_seam.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing Tecplot file .... Finished writing Tecplot file ok test_ff_cdfr (test_aflr4.TestAFLR4.test_ff_cdfr) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 ok test_invalid_Mesh_Lenght_Scale (test_aflr4.TestAFLR4.test_invalid_Mesh_Lenght_Scale) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 ok test_journal (test_aflr4.TestAFLR4.test_journal) ... ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) ok test_max_min_scale (test_aflr4.TestAFLR4.test_max_min_scale) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 ok test_phase (test_aflr4.TestAFLR4.test_phase) ... ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ok test_proximity (test_aflr4.TestAFLR4.test_proximity) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Getting mesh sizing parameters Mesh sizing name - Wing1 Mesh sizing name - Wing2 Done getting mesh sizing parameters AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Getting mesh sizing parameters Mesh sizing name - Wing1 Mesh sizing name - Wing2 Done getting mesh sizing parameters ok test_quad (test_aflr4.TestAFLR4.test_quad) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file ok test_reenter (test_aflr4.TestAFLR4.test_reenter) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk surface file .... capsGroups found: 1: Farfield 2: Wing1 Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk surface file .... capsGroups found: 1: Farfield 2: Wing1 Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file ok test_regions (test_aflr4.TestAFLR4.test_regions) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = cut, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk surface file .... capsGroups found: 1: box 2: cut Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file ok test_setInput (test_aflr4.TestAFLR4.test_setInput) ... ok test_skin (test_aflr4.TestAFLR4.test_skin) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Ribs, index = 1 Name = Skin, index = 2 Name = Spar1, index = 3 Name = Rib_Root, index = 4 Name = Spar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = LeadingEdge, index = 1 Name = TrailingEdge, index = 2 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk surface file .... capsGroups found: 1: Ribs 2: Skin 3: Spar1 4: Rib_Root 5: Spar2 Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file ok test_sphere (test_aflr4.TestAFLR4.test_sphere) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = sphere, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_torus (test_aflr4.TestAFLR4.test_torus) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = torus, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_Aeroelastic (test_astros.TestAstros.test_Aeroelastic) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Rib_Root, index = 1 Name = Skin, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 1 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 46 Number of elements = 44 Number of triangle elements = 0 Number of quadrilateral elements = 44 ---------------------------- Total number of nodes = 47 Total number of elements = 44 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root_Point, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = Skin_Top, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = Rib_Root, index = 1 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Rib_Root, index = 1 Name = Skin, index = 2 Name = Wing, index = 3 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Rib_Root, index = 1 Name = Skin, index = 2 Name = Wing, index = 3 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 46 Number of elements = 44 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 44 Combining multiple FEA meshes! Combined Number of nodal coordinates = 47 Combined Number of elements = 45 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 44 Getting vortex lattice surface data VLM surface name - Skin_Top Done getting vortex lattice surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 3 Surface 2: Number of points found for aero-spline = 6 (Re-)Combining all aerodynamic surfaces into a 'Wing', 'Canard', and/or 'Fin' single surfaces ! Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Rib_Root No "material" specified for Property tuple Rib_Root, defaulting to an index of 1 Property name - Skin No "material" specified for Property tuple Skin, defaulting to an index of 1 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - ribConstraint No "constraintType" specified for Constraint tuple ribConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA supports....... Number of supports - 1 Support name - ribSupport Done getting FEA supports Getting FEA connections....... Number of connection tuples - 1 Connection name - Rib_Root No "groupName" specified for Connection tuple Rib_Root! Looking for automatic connections from the use of capsConnectLink for Rib_Root 8 automatic connections were made for capsConnect Rib_Root (node id 1) Done getting FEA connections Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Trim1 Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing connection cards - appending mesh file Writing Astros instruction file.... Writing aeros card Writing analysis cards Writing constraint cards--each subcase individually Writing support cards Writing material cards Writing property cards Writing aeroelastic cards Running Astros...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Done running Astros! ok test_Plate (test_astros.TestAstros.test_Plate) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Face 1 TFI quading disabled with attribute .qParams Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 25 Number of elements = 16 Number of triangle elements = 0 Number of quadrilateral elements = 16 ---------------------------- Total number of nodes = 25 Total number of elements = 16 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plate, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 25 Number of elements = 16 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 16 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedPressure Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Astros grid and connectivity file .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedPressure Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedPressure Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ok test_MassProp_Units (test_avl.TestAVL.test_MassProp_Units) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing surface - Wing (ID = 0) Section 1 of 4 (ID = 3) Control surface 1 of 1 Section 2 of 4 (ID = 2) Control surface 1 of 1 Section 3 of 4 (ID = 1) Control surface 1 of 1 Section 4 of 4 (ID = 0) Control surface 1 of 1 Writing mass properties file: caps.mass Parsing MassProp Note: The following floating-point exceptions are signalling: IEEE_DIVIDE_BY_ZERO Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Note: The following floating-point exceptions are signalling: IEEE_DIVIDE_BY_ZERO Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp ok test_MassProp_noUnits (test_avl.TestAVL.test_MassProp_noUnits) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing surface - Wing (ID = 0) Section 1 of 4 (ID = 3) Control surface 1 of 1 Section 2 of 4 (ID = 2) Control surface 1 of 1 Section 3 of 4 (ID = 1) Control surface 1 of 1 Section 4 of 4 (ID = 0) Control surface 1 of 1 Writing mass properties file: caps.mass Parsing MassProp Note: The following floating-point exceptions are signalling: IEEE_DIVIDE_BY_ZERO Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Note: The following floating-point exceptions are signalling: IEEE_DIVIDE_BY_ZERO Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing mass properties file: caps.mass Parsing MassProp ok test_alpha_custom_increment (test_avl.TestAVL.test_alpha_custom_increment) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing surface - Wing (ID = 0) Section 1 of 4 (ID = 3) Control surface 1 of 1 Section 2 of 4 (ID = 2) Control surface 1 of 1 Section 3 of 4 (ID = 1) Control surface 1 of 1 Section 4 of 4 (ID = 0) Control surface 1 of 1 Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. ok test_geom_change (test_avl.TestAVL.test_geom_change) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing surface - Wing (ID = 0) Section 1 of 4 (ID = 3) Control surface 1 of 1 Section 2 of 4 (ID = 2) Control surface 1 of 1 Section 3 of 4 (ID = 1) Control surface 1 of 1 Section 4 of 4 (ID = 0) Control surface 1 of 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing surface - Wing (ID = 0) Section 1 of 4 (ID = 3) Control surface 1 of 1 Section 2 of 4 (ID = 2) Control surface 1 of 1 Section 3 of 4 (ID = 1) Control surface 1 of 1 Section 4 of 4 (ID = 0) Control surface 1 of 1 ok test_numSpan (test_avl.TestAVL.test_numSpan) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing ok test_phase (test_avl.TestAVL.test_phase) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing surface - Wing (ID = 0) Section 1 of 4 (ID = 3) Control surface 1 of 1 Section 2 of 4 (ID = 2) Control surface 1 of 1 Section 3 of 4 (ID = 1) Control surface 1 of 1 Section 4 of 4 (ID = 0) Control surface 1 of 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. ok test_wing_Vtail (test_avl.TestAVL.test_wing_Vtail) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - VTail1 No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - VTail2 No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Writing surface - VTail1 (ID = 0) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - VTail2 (ID = 1) Section 1 of 2 (ID = 0) Section 2 of 2 (ID = 1) Writing surface - Wing (ID = 2) Section 1 of 4 (ID = 3) Control surface 1 of 1 Section 2 of 4 (ID = 2) Control surface 1 of 1 Section 3 of 4 (ID = 1) Control surface 1 of 1 Section 4 of 4 (ID = 0) Control surface 1 of 1 ok test_wing_tail (test_avl.TestAVL.test_wing_tail) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice surface data VLM surface name - Wing VLM surface name - hTail VLM surface name - vTail No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control RightAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control LeftAileron not found in controls tuple! Only defaults will be used. Warning: Control Elevator not found in controls tuple! Only defaults will be used. Warning: Control Elevator not found in controls tuple! Only defaults will be used. Warning: Control Elevator not found in controls tuple! Only defaults will be used. Warning: Control Rudder not found in controls tuple! Only defaults will be used. Warning: Control Rudder not found in controls tuple! Only defaults will be used. Writing surface - Wing (ID = 0) Section 1 of 4 (ID = 3) Control surface 1 of 1 Section 2 of 4 (ID = 2) Control surface 1 of 1 Section 3 of 4 (ID = 1) Control surface 1 of 1 Section 4 of 4 (ID = 0) Control surface 1 of 1 Writing surface - hTail (ID = 1) Section 1 of 3 (ID = 2) Control surface 1 of 1 Section 2 of 3 (ID = 1) Control surface 1 of 1 Section 3 of 3 (ID = 0) Control surface 1 of 1 Writing surface - vTail (ID = 2) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 ok test_wing_tail_control (test_avl.TestAVL.test_wing_tail_control) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Wing, index = 1 Name = hTail, index = 2 Name = vTail, index = 3 Name = VTail1, index = 4 Name = VTail2, index = 5 Getting vortex lattice control surface data VLM control surface name - Elevator VLM control surface name - LeftAileron VLM control surface name - RightAileron VLM control surface name - Rudder Done getting vortex lattice control surface data Getting vortex lattice surface data VLM surface name - Wing VLM surface name - hTail VLM surface name - vTail No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Wing (ID = 0) Section 1 of 4 (ID = 3) Control surface 1 of 1 Section 2 of 4 (ID = 2) Control surface 1 of 1 Section 3 of 4 (ID = 1) Control surface 1 of 1 Section 4 of 4 (ID = 0) Control surface 1 of 1 Writing surface - hTail (ID = 1) Section 1 of 3 (ID = 2) Control surface 1 of 1 Section 2 of 3 (ID = 1) Control surface 1 of 1 Section 3 of 3 (ID = 0) Control surface 1 of 1 Writing surface - vTail (ID = 2) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 ok test_TargetCL (test_cart3d.TestCart3D.test_TargetCL) ... skipped 'No flowCart executable' test_outputs (test_cart3d.TestCart3D.test_outputs) ... skipped 'No flowCart executable' test_reenter (test_cart3d.TestCart3D.test_reenter) ... skipped 'No flowCart executable' test_sensitivity_AnalysisIn (test_cart3d.TestCart3D.test_sensitivity_AnalysisIn) ... skipped 'No flowCart executable' test_sensitivity_GeometryIn (test_cart3d.TestCart3D.test_sensitivity_GeometryIn) ... skipped 'No flowCart executable' test_Output_v5 (test_cbaero.TestCBAERO.test_Output_v5) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing1, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = riteWing, index = 1 Name = leftWing, index = 2 Name = trailingEdge, index = 3 Writing FAST file .... Finished writing FAST file Writing CBAero input file - cbaero_CAPS.cbaero Writing CBAero tagged regions - TaggedRegions Writing CBAero setup file - cbaero_CAPS.stp ok test_Output_v6 (test_cbaero.TestCBAERO.test_Output_v6) ... Writing CBAero input file - cbaero_CAPS.cbaero Writing CBAero tagged regions - TaggedRegions Writing CBAero setup file - cbaero_CAPS.stp ok test_inputs (test_cbaero.TestCBAERO.test_inputs) ... Writing CBAero input file - cbaero_CAPS.cbaero Writing CBAero tagged regions - TaggedRegions Writing CBAero setup file - cbaero_CAPS.stp ok test_MultiBody (test_egadsTess.TestEGADS.test_MultiBody) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters ok test_SingleBody_AnalysisOutVal (test_egadsTess.TestEGADS.test_SingleBody_AnalysisOutVal) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters ok test_all (test_egadsTess.TestEGADS.test_all) ... ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 9 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Name = nodeBody, index = 8 Name = farfield, index = 9 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 110333E00 EGADS Info: Face #3 -> Edge #9 (9) Internally in Loop 4 7, sen = -1! 110333E00 EGADS Info: Face #3 -> Edge #9 (9) Internally in Loop 7 4, sen = 1! 70000AC77000 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 7 4, sen = -1! 70000AC77000 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 4 7, sen = 1! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 9 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Name = nodeBody, index = 8 Name = farfield, index = 9 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 110333E00 EGADS Info: Face #3 -> Edge #9 (9) Internally in Loop 4 7, sen = -1! 70000AC77000 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 7 4, sen = -1! 70000AC77000 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 4 7, sen = 1! 110333E00 EGADS Info: Face #3 -> Edge #9 (9) Internally in Loop 7 4, sen = 1! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 9 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Name = nodeBody, index = 8 Name = farfield, index = 9 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 70000AC77000 EGADS Info: Face #3 -> Edge #9 (9) Internally in Loop 4 7, sen = -1! 70000AC77000 EGADS Info: Face #3 -> Edge #9 (9) Internally in Loop 7 4, sen = 1! 70000AC77000 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 7 4, sen = -1! 70000AC77000 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 4 7, sen = 1! ok test_box (test_egadsTess.TestEGADS.test_box) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 ok test_boxhole (test_egadsTess.TestEGADS.test_boxhole) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = boxhole, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 70000AC77000 EGADS Info: Face #3 -> Edge #9 (9) Internally in Loop 4 7, sen = -1! 70000AC77000 EGADS Info: Face #3 -> Edge #9 (9) Internally in Loop 7 4, sen = 1! 110333E00 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 7 4, sen = -1! 110333E00 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 4 7, sen = 1! ok test_bullet (test_egadsTess.TestEGADS.test_bullet) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = bullet, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_cone (test_egadsTess.TestEGADS.test_cone) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = cone, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_cylinder (test_egadsTess.TestEGADS.test_cylinder) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = cylinder, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_invalid_Mesh_Lenght_Scale (test_egadsTess.TestEGADS.test_invalid_Mesh_Lenght_Scale) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 ok test_journal (test_egadsTess.TestEGADS.test_journal) ... ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) ok test_nodeBody (test_egadsTess.TestEGADS.test_nodeBody) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = nodeBody, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_phase (test_egadsTess.TestEGADS.test_phase) ... ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters ERROR:: BAD STATUS = -276 from matsol (called from solveSketchOrig:63376) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Getting mesh sizing parameters Mesh sizing name - box Done getting mesh sizing parameters ok test_reenter (test_egadsTess.TestEGADS.test_reenter) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk surface file .... capsGroups found: 1: Farfield 2: Wing1 Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk surface file .... capsGroups found: 1: Farfield 2: Wing1 Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file ok test_setInput (test_egadsTess.TestEGADS.test_setInput) ... EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! ok test_sphere (test_egadsTess.TestEGADS.test_sphere) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = sphere, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_torus (test_egadsTess.TestEGADS.test_torus) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = torus, index = 1 Name = farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 ok test_Design_SensFile (test_fun3d.TestFUN3D.test_Design_SensFile) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 6751 Number of elements = 13498 Number of triangle elements = 13498 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 4919 Number of elements = 9834 Number of triangle elements = 9834 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 196 Number of elements = 388 Number of triangle elements = 388 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11866 Total number of elements = 23720 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 11866, elements - 23720 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.138613 Creating surface mesh ... Surface mesh seconds: 0.034878 Recovering boundaries... Boundary recovery seconds: 0.135883 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.055207 Recovering Delaunayness... Delaunay recovery seconds: 0.067403 Refining mesh... 15817 insertions, added 8076 points, 516596 tetrahedra in queue. 5267 insertions, added 1612 points, 522415 tetrahedra in queue. 7020 insertions, added 1839 points, 496219 tetrahedra in queue. 9358 insertions, added 1649 points, 350840 tetrahedra in queue. 12474 insertions, added 1188 points, 9687 tetrahedra in queue. 16628 insertions, added 1422 points, 5458 tetrahedra in queue. Refinement seconds: 8.9361 Smoothing vertices... Mesh smoothing seconds: 1.92933 Improving mesh... Mesh improvement seconds: 0.051271 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.018509 Total running seconds: 11.3685 Statistics: Input points: 11866 Input facets: 23720 Input segments: 35580 Input holes: 2 Input regions: 0 Mesh points: 28105 Mesh tetrahedra: 135725 Mesh faces: 283310 Mesh faces on exterior boundary: 23720 Mesh faces on input facets: 23720 Mesh edges on input segments: 35580 Steiner points inside domain: 16239 Done meshing using TetGen! Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Getting CFD design variables....... Number of design variables - 5 Design Variable name - Mach Warning: No initial value set for Mach Design Variable name - area Design Variable name - aspect Design Variable name - taper Design Variable name - twist Done getting CFD design variables Python library was linked, but will not be used! Creating FUN3D directory tree Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. ok test_Design_Sensitivity (test_fun3d.TestFUN3D.test_Design_Sensitivity) ... Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Getting CFD design variables....... Number of design variables - 6 Design Variable name - Alpha Design Variable name - Beta Warning: No initial value set for Beta Design Variable name - area Design Variable name - aspect Design Variable name - taper Design Variable name - twist Done getting CFD design variables Getting CFD functional....... Number of design variables - 2 Objective name - Composite Objective name - Lift^2 Done getting CFD functional Python library was linked, but will not be used! Creating FUN3D directory tree Writing rubber.data Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Reading rubber.data Creating FUN3D directory tree DesignVariable = Alpha DesignVariable = Beta DesignVariable = area DesignVariable = aspect DesignVariable = taper DesignVariable = twist Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1 Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1 Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1 Writing rubber.data Writing MAPBC file .... Finished writing MAPBC file Using Python to write FUN3D namelist (fun3d.nml) Overwrite_NML is set to 'True' - a new namelist will be created Creating namelist Done writing nml file with Python Info: No recognized data transfer names found. Reading rubber.data Getting CFD design variables....... Number of design variables - 1 Design Variable name - Alpha Done getting CFD design variables Getting CFD functional....... Number of design variables - 2 Objective name - Composite Objective name - Lift^2 Done getting CFD functional Creating FUN3D directory tree DesignVariable = Alpha Writing rubber.data Writing MAPBC file .... Finished writing MAPBC file Using Python to write FUN3D namelist (fun3d.nml) Overwrite_NML is set to 'True' - a new namelist will be created Creating namelist Done writing nml file with Python Info: No recognized data transfer names found. Reading rubber.data ok test_Mesh_Morph_Sensitivity (test_fun3d.TestFUN3D.test_Mesh_Morph_Sensitivity) ... Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Getting CFD design variables....... Number of design variables - 6 Design Variable name - Alpha Design Variable name - Beta Warning: No initial value set for Beta Design Variable name - area Design Variable name - aspect Design Variable name - taper Design Variable name - twist Done getting CFD design variables Getting CFD functional....... Number of design variables - 2 Objective name - Composite Objective name - Lift^2 Done getting CFD functional Python library was linked, but will not be used! Creating FUN3D directory tree DesignVariable = Alpha DesignVariable = Beta DesignVariable = area DesignVariable = aspect DesignVariable = taper DesignVariable = twist Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1 Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1 Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1 Writing rubber.data Writing surface file for 1 (of 3) in body 1 File - Flow/fun3d_CAPS_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3d_CAPS_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3d_CAPS_body1.dat Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Reading rubber.data Projecting tessellation 1 (of 3) on to new body Projecting tessellation 2 (of 3) on to new body Projecting tessellation 3 (of 3) on to new body Python library was linked, but will not be used! Creating FUN3D directory tree DesignVariable = Alpha DesignVariable = Beta DesignVariable = area DesignVariable = aspect DesignVariable = taper DesignVariable = twist Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1 Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1 Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1 Writing surface file for 1 (of 3) in body 1 File - Flow/fun3d_CAPS_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3d_CAPS_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3d_CAPS_body1.dat Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Reading rubber.data Projecting tessellation 1 (of 3) on to new body Projecting tessellation 2 (of 3) on to new body Projecting tessellation 3 (of 3) on to new body Python library was linked, but will not be used! Creating FUN3D directory tree DesignVariable = Alpha DesignVariable = Beta DesignVariable = area DesignVariable = aspect DesignVariable = taper DesignVariable = twist Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1 Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1 Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1 Writing surface file for 1 (of 3) in body 1 File - Flow/fun3d_CAPS_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3d_CAPS_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3d_CAPS_body1.dat Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Reading rubber.data ok test_cythonNML (test_fun3d.TestFUN3D.test_cythonNML) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 6751 Number of elements = 13498 Number of triangle elements = 13498 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 4919 Number of elements = 9834 Number of triangle elements = 9834 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 196 Number of elements = 388 Number of triangle elements = 388 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11866 Total number of elements = 23720 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 11866, elements - 23720 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.129669 Creating surface mesh ... Surface mesh seconds: 0.037522 Recovering boundaries... Boundary recovery seconds: 0.129756 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.054077 Recovering Delaunayness... Delaunay recovery seconds: 0.062532 Refining mesh... 15817 insertions, added 8076 points, 516596 tetrahedra in queue. 5267 insertions, added 1612 points, 522415 tetrahedra in queue. 7020 insertions, added 1839 points, 496219 tetrahedra in queue. 9358 insertions, added 1649 points, 350840 tetrahedra in queue. 12474 insertions, added 1188 points, 9687 tetrahedra in queue. 16628 insertions, added 1422 points, 5458 tetrahedra in queue. Refinement seconds: 8.37202 Smoothing vertices... Mesh smoothing seconds: 2.14625 Improving mesh... Mesh improvement seconds: 0.037577 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.016446 Total running seconds: 10.9872 Statistics: Input points: 11866 Input facets: 23720 Input segments: 35580 Input holes: 2 Input regions: 0 Mesh points: 28105 Mesh tetrahedra: 135725 Mesh faces: 283310 Mesh faces on exterior boundary: 23720 Mesh faces on input facets: 23720 Mesh edges on input segments: 35580 Steiner points inside domain: 16239 Done meshing using TetGen! Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Writing MAPBC file .... Finished writing MAPBC file Using Python to write FUN3D namelist (fun3d.nml) Reading /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/src/CAPS/aim/unitTest/pyCAPS/workDir_fun3dTest/Scratch/fun3dAIM4/fun3d.nml ..... Appending namelist Done writing nml file with Python Info: No recognized data transfer names found. ok test_cythonNMLError (test_fun3d.TestFUN3D.test_cythonNMLError) ... ok test_cythonNMLReentrance (test_fun3d.TestFUN3D.test_cythonNMLReentrance) ... Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Writing MAPBC file .... Finished writing MAPBC file Using Python to write FUN3D namelist (fun3d.nml) /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/src/CAPS/aim/unitTest/pyCAPS/workDir_fun3dTest/Scratch/fun3dAIM6/fun3d.nml not found! Creating namelist Done writing nml file with Python Info: No recognized data transfer names found. Writing MAPBC file .... Finished writing MAPBC file Using Python to write FUN3D namelist (fun3d.nml) Reading /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/src/CAPS/aim/unitTest/pyCAPS/workDir_fun3dTest/Scratch/fun3dAIM6/fun3d.nml ..... Appending namelist Done writing nml file with Python Info: No recognized data transfer names found. ok test_invalidBoundary (test_fun3d.TestFUN3D.test_invalidBoundary) ... Getting CFD boundary conditions Boundary condition name - Wing1 ok test_invalidBoundaryName (test_fun3d.TestFUN3D.test_invalidBoundaryName) ... Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - X ok test_journal (test_fun3d.TestFUN3D.test_journal) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 1208, elements - 2404 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Getting CFD design variables....... Number of design variables - 4 Design Variable name - area Design Variable name - aspect Design Variable name - taper Design Variable name - twist Done getting CFD design variables Python library was linked, but will not be used! Creating FUN3D directory tree Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 1208, elements - 2404 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Getting CFD design variables....... Number of design variables - 4 Design Variable name - area Design Variable name - aspect Design Variable name - taper Design Variable name - twist Done getting CFD design variables Python library was linked, but will not be used! Creating FUN3D directory tree Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Getting CFD design variables....... Number of design variables - 4 Design Variable name - area Design Variable name - aspect Design Variable name - taper Design Variable name - twist Done getting CFD design variables CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! ok test_moving_body (test_fun3d.TestFUN3D.test_moving_body) ... Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Python library was linked, but will not be used! Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Writing moving_body.input ok test_overwriteNML (test_fun3d.TestFUN3D.test_overwriteNML) ... Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Python library was linked, but will not be used! Writing MAPBC file .... Finished writing MAPBC file Since Python was not linked and/or being used, the "Overwrite_NML" input needs to be set to "True" to give permission to create a new fun3d.nml. fun3d.nml will NOT be updated!! Info: No recognized data transfer names found. ok test_phase (test_fun3d.TestFUN3D.test_phase) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 11866, elements - 23720 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Python library was linked, but will not be used! Writing MAPBC file .... Finished writing MAPBC file Since Python was not linked and/or being used, the "Overwrite_NML" input needs to be set to "True" to give permission to create a new fun3d.nml. fun3d.nml will NOT be updated!! Info: No recognized data transfer names found. Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Python library was linked, but will not be used! Writing MAPBC file .... Finished writing MAPBC file Since Python was not linked and/or being used, the "Overwrite_NML" input needs to be set to "True" to give permission to create a new fun3d.nml. fun3d.nml will NOT be updated!! Info: No recognized data transfer names found. ok test_reenter (test_fun3d.TestFUN3D.test_reenter) ... Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Python library was linked, but will not be used! Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Python library was linked, but will not be used! Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. ok test_symmetry (test_fun3d.TestFUN3D.test_symmetry) ... Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Python library was linked, but will not be used! Writing MAPBC file .... Finished writing MAPBC file Since Python was not linked and/or being used, the "Overwrite_NML" input needs to be set to "True" to give permission to create a new fun3d.nml. fun3d.nml will NOT be updated!! Info: No recognized data transfer names found. ok test_box1 (test_masstran.TestMasstran.test_box1) ... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - box1 Done getting FEA properties Updating mesh element types based on properties input Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 7 Design_Variable name - H Design_Variable name - L Design_Variable name - W Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> L Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input ===> W Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input ===> H Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input ===> x0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> x1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> m0 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> m1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ok test_box2 (test_masstran.TestMasstran.test_box2) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1692 Number of elements = 3380 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3380 Elemental Quad4 = 0 Getting FEA properties....... Number of properties - 1 Property name - box1 Done getting FEA properties Updating mesh element types based on properties input Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 7 Design_Variable name - H Design_Variable name - L Design_Variable name - W Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> L Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Projecting tessellation 1 (of 1) on to new body Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1692 Number of elements = 3380 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3380 Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Projecting tessellation 1 (of 1) on to new body Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1692 Number of elements = 3380 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3380 Elemental Quad4 = 0 Updating mesh element types based on properties input ===> W Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Projecting tessellation 1 (of 1) on to new body Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1692 Number of elements = 3380 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3380 Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Projecting tessellation 1 (of 1) on to new body Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1692 Number of elements = 3380 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3380 Elemental Quad4 = 0 Updating mesh element types based on properties input ===> H Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Projecting tessellation 1 (of 1) on to new body Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1692 Number of elements = 3380 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3380 Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Projecting tessellation 1 (of 1) on to new body Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1692 Number of elements = 3380 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3380 Elemental Quad4 = 0 Updating mesh element types based on properties input ===> x0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Projecting tessellation 1 (of 1) on to new body Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1692 Number of elements = 3380 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3380 Elemental Quad4 = 0 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> x1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> m0 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> m1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ok test_box3 (test_masstran.TestMasstran.test_box3) ... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = box2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Getting FEA properties....... Number of properties - 2 Property name - box1 Property name - box2 Done getting FEA properties Updating mesh element types based on properties input Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 7 Design_Variable name - H Design_Variable name - L Design_Variable name - W Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Design_Variable_Relation name - thick_box2 Number of design variable relations - 4 Done getting FEA design variables ===> L Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = box2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = box2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input ===> W Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = box2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = box2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input ===> H Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = box2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = box2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input ===> x0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = box2, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2402 Number of elements = 2400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2400 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Design_Variable_Relation name - thick_box2 Number of design variable relations - 4 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Design_Variable_Relation name - thick_box2 Number of design variable relations - 4 Done getting FEA design variables ===> x1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Design_Variable_Relation name - thick_box2 Number of design variable relations - 4 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Design_Variable_Relation name - thick_box2 Number of design variable relations - 4 Done getting FEA design variables ===> m0 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Design_Variable_Relation name - thick_box2 Number of design variable relations - 4 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Design_Variable_Relation name - thick_box2 Number of design variable relations - 4 Done getting FEA design variables ===> m1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Design_Variable_Relation name - thick_box2 Number of design variable relations - 4 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Design_Variable_Relation name - thick_box2 Number of design variable relations - 4 Done getting FEA design variables ok test_journal (test_masstran.TestMasstran.test_journal) ... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 4332 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4332 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 4009 Number of elements = 8014 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 8014 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 6178 Combined Number of elements = 12347 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 12346 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - box1 Property name - point Done getting FEA properties Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 4332 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4332 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 4000 Number of elements = 7996 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 7996 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 6169 Combined Number of elements = 12329 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 12328 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 4332 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4332 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 4009 Number of elements = 8014 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 8014 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 6178 Combined Number of elements = 12347 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 12346 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - box1 Property name - point Done getting FEA properties Updating mesh element types based on properties input CAPS Info: Hit last success -- going live! Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 4332 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4332 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 4009 Number of elements = 8014 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 8014 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 6178 Combined Number of elements = 12347 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 12346 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - box1 Property name - point Done getting FEA properties Updating mesh element types based on properties input CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 4332 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4332 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 4000 Number of elements = 7996 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 7996 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 6169 Combined Number of elements = 12329 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 12328 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - box1 Property name - point Done getting FEA properties Updating mesh element types based on properties input CAPS Info: Hit last success -- going live! Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 4332 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4332 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 4000 Number of elements = 7996 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 7996 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 6169 Combined Number of elements = 12329 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 12328 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - box1 Property name - point Done getting FEA properties Updating mesh element types based on properties input ok test_plate (test_masstran.TestMasstran.test_plate) ... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Getting FEA properties....... Number of properties - 1 Property name - box1 Done getting FEA properties Updating mesh element types based on properties input Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 7 Design_Variable name - H Design_Variable name - L Design_Variable name - W Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> L Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Updating mesh element types based on properties input ===> W Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Updating mesh element types based on properties input ===> H Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Updating mesh element types based on properties input ===> x0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box1, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> x1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> m0 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ===> m1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 3 Done getting FEA design variables ok test_plate_point (test_masstran.TestMasstran.test_plate_point) ... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 442 Combined Number of elements = 401 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 400 Getting FEA properties....... Number of properties - 2 Property name - box1 Property name - point Done getting FEA properties Updating mesh element types based on properties input Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 7 Design_Variable name - H Design_Variable name - L Design_Variable name - W Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - mass_point Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 4 Done getting FEA design variables ===> L Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 442 Combined Number of elements = 401 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 442 Combined Number of elements = 401 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 400 Updating mesh element types based on properties input ===> W Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 442 Combined Number of elements = 401 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 442 Combined Number of elements = 401 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 400 Updating mesh element types based on properties input ===> H Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 442 Combined Number of elements = 401 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 400 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 442 Combined Number of elements = 401 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 400 Updating mesh element types based on properties input ===> x0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box1, index = 1 Name = point, index = 2 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 441 Number of elements = 400 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 400 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 442 Combined Number of elements = 401 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 400 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - mass_point Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 4 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - mass_point Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 4 Done getting FEA design variables ===> x1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - mass_point Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 4 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - mass_point Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 4 Done getting FEA design variables ===> m0 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - mass_point Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 4 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - mass_point Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 4 Done getting FEA design variables ===> m1 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - mass_point Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 4 Done getting FEA design variables Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 4 Design_Variable name - m0 Design_Variable name - m1 Design_Variable name - x0 Design_Variable name - x1 Design_Variable_Relation name - mass_point Design_Variable_Relation name - rho_madeupium Name madeupium not found in attribute map!!!! Design_Variable_Relation name - rho_unobtainium Name unobtainium not found in attribute map!!!! Design_Variable_Relation name - thick_box1 Number of design variable relations - 4 Done getting FEA design variables ok test_Cheby_Modes (test_mses.TestMSES_Kulfan.test_Cheby_Modes) ... Getting CFD design variables....... Number of design variables - 4 Design Variable name - alowervar Design Variable name - auppervar Design Variable name - classvar Design Variable name - ztailvar Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 ok test_Cheby_Modes_Symmetric (test_mses.TestMSES_Kulfan.test_Cheby_Modes_Symmetric) ... Getting CFD design variables....... Number of design variables - 1 Design Variable name - avar Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 ok test_allInputs (test_mses.TestMSES_Kulfan.test_allInputs) ... ok test_execute (test_mses.TestMSES_Kulfan.test_execute) ... ok test_sensitivity_AnalysisIn (test_mses.TestMSES_Kulfan.test_sensitivity_AnalysisIn) ... ok test_Cheby_Modes_Symmetric (test_mses.TestMSES_NACA.test_Cheby_Modes_Symmetric) ... Getting CFD design variables....... Number of design variables - 1 Design Variable name - thick Done getting CFD design variables ok test_geom_sensitivity_CL (test_mses.TestMSES_NACA.test_geom_sensitivity_CL) ... Getting CFD design variables....... Number of design variables - 2 Design Variable name - camber Design Variable name - thick Done getting CFD design variables ok test_journal (test_mses.TestMSES_NACA.test_journal) ... Getting CFD design variables....... Number of design variables - 1 Design Variable name - thick Done getting CFD design variables EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Getting CFD design variables....... Number of design variables - 1 Design Variable name - thick Done getting CFD design variables CAPS Info: Hit last success -- going live! Getting CFD design variables....... Number of design variables - 1 Design Variable name - thick Done getting CFD design variables CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Getting CFD design variables....... Number of design variables - 1 Design Variable name - thick Done getting CFD design variables CAPS Info: Hit last success -- going live! Getting CFD design variables....... Number of design variables - 1 Design Variable name - thick Done getting CFD design variables ok test_MultiBody (test_pointwise.TestPointwise.test_MultiBody) ... skipped 'No pointwise executable' test_SingleBody (test_pointwise.TestPointwise.test_SingleBody) ... skipped 'No pointwise executable' test_all (test_pointwise.TestPointwise.test_all) ... skipped 'No pointwise executable' test_box (test_pointwise.TestPointwise.test_box) ... skipped 'No pointwise executable' test_bullet (test_pointwise.TestPointwise.test_bullet) ... skipped 'No pointwise executable' test_cone (test_pointwise.TestPointwise.test_cone) ... skipped 'No pointwise executable' test_cylinder (test_pointwise.TestPointwise.test_cylinder) ... skipped 'No pointwise executable' test_executeError (test_pointwise.TestPointwise.test_executeError) ... skipped 'No pointwise executable' test_reenter (test_pointwise.TestPointwise.test_reenter) ... skipped 'No pointwise executable' test_sphere (test_pointwise.TestPointwise.test_sphere) ... skipped 'No pointwise executable' EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! test_Area_Mesh (test_refine.TestREFINE.test_Area_Mesh) ... Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 54 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 54 54 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 12 26 AFLR2 IG : Nodes, Faces = 24 50 AFLR2 IG : Nodes, Faces = 36 74 AFLR2 IG : Nodes, Faces = 48 98 AFLR2 IG : Nodes, Faces = 52 106 AFLR2 IG : Nodes, Faces = 53 108 AFLR2 IG : Nodes, Faces = 54 110 AFLR2 IG : Nodes, Faces = 58 110 AFLR2 IG : Nodes, Faces = 54 54 AFLR2 : CPU Time = 0.000 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 54 54 AFLR2 GG : Nodes, Faces = 100 146 AFLR2 GG : Nodes, Faces = 122 190 AFLR2 GG : Nodes, Faces = 138 222 AFLR2 GG : Nodes, Faces = 153 252 AFLR2 GG : Nodes, Faces = 168 282 AFLR2 GG : Nodes, Faces = 180 306 AFLR2 GG : Nodes, Faces = 192 330 AFLR2 GG : Nodes, Faces = 201 348 AFLR2 GG : Nodes, Faces = 210 366 AFLR2 GG : Nodes, Faces = 216 378 AFLR2 GG : Nodes, Faces = 221 388 AFLR2 GG : Nodes, Faces = 224 394 AFLR2 GG : Nodes, Faces = 225 396 AFLR2 : CPU Time = 0.000 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 225 396 AFLR2 : CPU Time = 0.000 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 225 Number of elements = 450 Number of tris = 396 Number of quad = 0 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file ok test_all (test_refine.TestREFINE.test_all) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = farfield, index = 1 Name = box, index = 2 Name = sphere, index = 3 Name = boxhole, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = farfield, index = 1 Name = box, index = 2 Name = sphere, index = 3 Name = boxhole, index = 4 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 1665 Number of elements = 9143 Number of triangles = 1216 Number of quadrilatarals = 0 Number of tetrahedrals = 7927 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 ok test_box_volume (test_refine.TestREFINE.test_box_volume) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = box, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = box, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 2600 Number of elements = 13864 Number of triangles = 2758 Number of quadrilatarals = 0 Number of tetrahedrals = 11106 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 ok test_boxhole (test_refine.TestREFINE.test_boxhole) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = boxhole, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = boxhole, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 1071 Number of elements = 5705 Number of triangles = 998 Number of quadrilatarals = 0 Number of tetrahedrals = 4707 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 ok test_cfdSingleBody (test_refine.TestREFINE.test_cfdSingleBody) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 20272 Number of elements = 117350 Number of triangles = 5384 Number of quadrilatarals = 0 Number of tetrahedrals = 111966 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Done getting CFD boundary conditions Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 1 Done boundary flags Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Done getting CFD boundary conditions Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 1 Done boundary flags Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Done getting CFD boundary conditions Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 1 Done boundary flags Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" ok test_fun3d (test_refine.TestREFINE.test_fun3d) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = farfield, index = 1 Name = box, index = 2 Name = sphere, index = 3 Name = boxhole, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = farfield, index = 1 Name = box, index = 2 Name = sphere, index = 3 Name = boxhole, index = 4 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 1665 Number of elements = 9143 Number of triangles = 1216 Number of quadrilatarals = 0 Number of tetrahedrals = 7927 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 ok test_inputs (test_refine.TestREFINE.test_inputs) ... ok test_phase (test_refine.TestREFINE.test_phase) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = box, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = box, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 438 Number of elements = 2179 Number of triangles = 644 Number of quadrilatarals = 0 Number of tetrahedrals = 1535 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = box, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 1 Name = box, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = box, index = 2 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = box, index = 2 ok test_sphere (test_refine.TestREFINE.test_sphere) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = sphere, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = farfield, index = 1 Name = sphere, index = 2 Getting volume mesh EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 936 Number of elements = 4999 Number of triangles = 758 Number of quadrilatarals = 0 Number of tetrahedrals = 4241 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 ok test_inputs (test_su2.TestSU2.test_inputs) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting volume mesh UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 3 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 8 Faces EGADS : Body 0 has 15 Edges EGADS : Body 0 has 8 Loops EGADS : Body 0 has 9 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 8 Faces EGADS : Body 1 has 15 Edges EGADS : Body 1 has 8 Loops EGADS : Body 1 has 9 Nodes EGADS : Body 2 is a SolidBody EGADS : Body 2 has 1 Shells EGADS : Body 2 has 2 Faces EGADS : Body 2 has 6 Edges EGADS : Body 2 has 2 Loops EGADS : Body 2 has 2 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 1 1 2 3 4 5 EGADS : 2 Yes 0 0 1 1 1 1 3 4 6 EGADS : 3 Yes 0 0 1 1 1 1 2 4 7 EGADS : 4 Yes 0 0 1 1 1 1 2 3 EGADS : 5 Yes 0 0 1 1 1 1 6 7 8 EGADS : 6 Yes 0 0 1 1 1 2 5 7 8 EGADS : 7 Yes 0 0 1 1 1 3 5 6 8 EGADS : 8 Yes 0 0 1 1 1 5 6 7 EGADS : 9 Yes 1 0 1 0 10 10 11 12 13 EGADS : 10 Yes 1 0 1 0 10 9 11 12 14 EGADS : 11 Yes 1 0 1 0 10 9 10 12 15 EGADS : 12 Yes 1 0 1 0 10 9 10 11 EGADS : 13 Yes 1 0 1 0 10 9 14 15 16 EGADS : 14 Yes 1 0 1 0 10 10 13 15 16 EGADS : 15 Yes 1 0 1 0 10 11 13 14 16 EGADS : 16 Yes 1 0 1 0 10 13 14 15 EGADS : 17 Yes 2 0 1 NA NA 18 EGADS : 18 Yes 2 0 1 NA NA 17 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 1 4 -3 -2 EGADS : 2 3 7 -6 -5 EGADS : 3 6 9 -1 -8 EGADS : 4 -4 -9 -7 EGADS : 5 -10 2 11 -12 EGADS : 6 -11 5 13 -14 EGADS : 7 -13 8 10 -15 EGADS : 8 12 14 15 EGADS : 9 16 19 -18 -17 EGADS : 10 18 22 -21 -20 EGADS : 11 21 24 -16 -23 EGADS : 12 -19 -24 -22 EGADS : 13 -25 17 26 -27 EGADS : 14 -26 20 28 -29 EGADS : 15 -28 23 25 -30 EGADS : 16 27 29 30 EGADS : 17 -31 -32 33 34 EGADS : 18 -35 -34 36 32 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : 17 17 EGADS : 18 18 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes 1 4 -3 -2 EGADS : 2 Yes 3 7 -6 -5 EGADS : 3 Yes 6 9 -1 -8 EGADS : 4 Yes -4 -9 -7 EGADS : 5 Yes -10 2 11 -12 EGADS : 6 Yes -11 5 13 -14 EGADS : 7 Yes -13 8 10 -15 EGADS : 8 Yes 12 14 15 EGADS : 9 Yes 16 19 -18 -17 EGADS : 10 Yes 18 22 -21 -20 EGADS : 11 Yes 21 24 -16 -23 EGADS : 12 Yes -19 -24 -22 EGADS : 13 Yes -25 17 26 -27 EGADS : 14 Yes -26 20 28 -29 EGADS : 15 Yes -28 23 25 -30 EGADS : 16 Yes 27 29 30 EGADS : 17 Yes -31 -32 33 34 EGADS : 18 Yes -35 -34 36 32 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 5 EGADS : 3 0 Yes 3 4 1 1 2 EGADS : 4 0 Yes 2 4 1 1 4 EGADS : 5 0 Yes 3 5 1 2 6 EGADS : 6 0 Yes 5 6 1 2 3 EGADS : 7 0 Yes 4 6 1 2 4 EGADS : 8 0 Yes 5 1 1 3 7 EGADS : 9 0 Yes 6 2 1 3 4 EGADS : 10 0 Yes 1 7 1 5 7 EGADS : 11 0 Yes 3 8 1 5 6 EGADS : 12 0 Yes 7 8 1 5 8 EGADS : 13 0 Yes 5 9 1 6 7 EGADS : 14 0 Yes 8 9 1 6 8 EGADS : 15 0 Yes 9 7 1 7 8 EGADS : 16 1 Yes 10 11 1 9 11 EGADS : 17 1 Yes 10 12 1 9 13 EGADS : 18 1 Yes 12 13 1 9 10 EGADS : 19 1 Yes 11 13 1 9 12 EGADS : 20 1 Yes 12 14 1 10 14 EGADS : 21 1 Yes 14 15 1 10 11 EGADS : 22 1 Yes 13 15 1 10 12 EGADS : 23 1 Yes 14 10 1 11 15 EGADS : 24 1 Yes 15 11 1 11 12 EGADS : 25 1 Yes 10 16 1 13 15 EGADS : 26 1 Yes 12 17 1 13 14 EGADS : 27 1 Yes 16 17 1 13 16 EGADS : 28 1 Yes 14 18 1 14 15 EGADS : 29 1 Yes 17 18 1 14 16 EGADS : 30 1 Yes 18 16 1 15 16 EGADS : 31 2 DEGEN 19 19 - 17 EGADS : 32 2 Yes 20 19 NA 17 18 EGADS : 33 2 DEGEN 20 20 - 17 EGADS : 34 2 Yes 20 19 NA 17 18 EGADS : 35 2 DEGEN 19 19 - 18 EGADS : 36 2 DEGEN 20 20 - 18 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 3.77246052 0 0.00459131419 EGADS : 2 Yes 5.90487498 7.07106781 0 EGADS : 3 Yes 0 0 0 EGADS : 4 Yes 4.0824829 7.07106781 0.123425948 EGADS : 5 Yes 3.77001182 0 0 EGADS : 6 Yes 5.90282524 7.07106781 0 EGADS : 7 Yes 5.90487498 0 0 EGADS : 8 Yes 4.0824829 0 0.123425948 EGADS : 9 Yes 5.90282524 0 0 EGADS : 10 Yes 15.2802204 0 0.00183652568 EGADS : 11 Yes 16.1331862 2.82842712 0 EGADS : 12 Yes 13.7712362 0 0 EGADS : 13 Yes 15.4042293 2.82842712 0.0493703791 EGADS : 14 Yes 15.2792409 0 0 EGADS : 15 Yes 16.1323663 2.82842712 0 EGADS : 16 Yes 16.1331862 0 0 EGADS : 17 Yes 15.4042293 0 0.0493703791 EGADS : 18 Yes 16.1323663 0 0 EGADS : 19 Yes 0 0 80 EGADS : 20 Yes 0 0 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 160 AFLR4 : Min Bounding Box Length = 160 AFLR4 : Max Ref Bounding Box Length = 16.1372 AFLR4 : Min Ref Bounding Box Length = 0.890888 AFLR4 : Reference Length = 0.890888 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 14.7419 AFLR4 : Abs Min Surf Spacing = 0.00222722 AFLR4 : Min Surf Spacing = 0.00445444 AFLR4 : Max Surf Spacing = 0.0890888 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD AFLR4 : 2 CAD geometry 0 STD AFLR4 : 3 CAD geometry 0 STD AFLR4 : 4 CAD geometry 0 STD AFLR4 : 5 CAD geometry 0 STD AFLR4 : 6 CAD geometry 0 STD AFLR4 : 7 CAD geometry 0 STD AFLR4 : 8 CAD geometry 0 STD AFLR4 : 9 CAD geometry 0 STD AFLR4 : 10 CAD geometry 0 STD AFLR4 : 11 CAD geometry 0 STD AFLR4 : 12 CAD geometry 0 STD AFLR4 : 13 CAD geometry 0 STD AFLR4 : 14 CAD geometry 0 STD AFLR4 : 15 CAD geometry 0 STD AFLR4 : 16 CAD geometry 0 STD AFLR4 : 17 CAD geometry 0 FARFIELD AFLR4 : 18 CAD geometry 0 FARFIELD AFLR4 : Case has 2 Proximity Checking Components AFLR4 : Component 1 includes Definitions 1 2 3 4 5 6 7 8 AFLR4 : Component 2 includes Definitions 9 10 11 12 13 14 15 16 AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Define CAD surface definition 17 AFLR4 : Define CAD surface definition 18 AFLR43 : INPUT SURFACE MESH FROM TESS AFLR43 : Quad Surface Faces= 0 AFLR43 : Tria Surface Faces= 11696 AFLR43 : Nodes = 5854 UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR3 : --------------------------------------- AFLR3 : AFLR3 LIBRARY AFLR3 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR3 : TETRAHEDRAL GRID GENERATOR AFLR3 : Version Number 16.32.50 AFLR3 : Version Date 10/31/23 @ 06:31PM AFLR3 : Compile OS Darwin 22.6.0 x86_64 AFLR3 : Compile Date 11/01/23 @ 12:19PM AFLR3 : Copyright 1994-2021, D.L. Marcum AFLR3 : --------------------------------------- AFLR3 IC : INPUT SURFACE GRID CHECK AFLR3 IC : Nodes, Elements = 5854 0 UG3 : Boundary Conditions UG3 : B-Face ID Boundary Condition UG3 : 1 Solid UG3 : 2 Solid UG3 : 3 Solid UG3 : 4 Solid UG3 : 5 Solid UG3 : 6 Solid UG3 : 7 Solid UG3 : 8 Solid UG3 : 9 Solid UG3 : 10 Solid UG3 : 11 Solid UG3 : 12 Solid UG3 : 13 Solid UG3 : 14 Solid UG3 : 15 Solid UG3 : 16 Solid UG3 : 17 FarField UG3 : 18 FarField AFLR3 : CPU Time = 0.016 seconds AFLR3 IG : INITIAL VOLUME GRID GENERATION AFLR3 IG : Nodes, Elements = 5854 0 AFLR3 IG : Nodes, Elements = 8 10 AFLR3 IG : Nodes, Elements = 1172 6979 AFLR3 IG : Nodes, Elements = 2344 15144 AFLR3 IG : Nodes, Elements = 3516 23433 AFLR3 IG : Nodes, Elements = 4688 31724 AFLR3 IG : Nodes, Elements = 5860 39971 AFLR3 IG : Nodes, Elements = 5861 39980 AFLR3 IG : Nodes, Elements = 5861 39927 AFLR3 IG : Nodes, Elements = 5861 39954 AFLR3 IG : Nodes, Elements = 5861 39928 AFLR3 IG : Nodes, Elements = 5854 23732 AFLR3 IG : Nodes, Elements = 5854 23747 AFLR3 IG : Nodes, Elements = 5854 19617 AFLR3 IG : Nodes, Elements = 5854 17611 AFLR3 : CPU Time = 0.165 seconds AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION AFLR3 GG : Nodes, Elements = 5854 17611 AFLR3 GG : Nodes, Elements = 8532 25853 AFLR3 GG : Nodes, Elements = 8532 37006 AFLR3 GG : Nodes, Elements = 8532 34255 AFLR3 GG : Nodes, Elements = 8532 32797 AFLR3 GG : Nodes, Elements = 10906 40277 AFLR3 GG : Nodes, Elements = 10906 50546 AFLR3 GG : Nodes, Elements = 10906 47482 AFLR3 GG : Nodes, Elements = 10906 46581 AFLR3 GG : Nodes, Elements = 13450 54531 AFLR3 GG : Nodes, Elements = 13450 65541 AFLR3 GG : Nodes, Elements = 13450 62498 AFLR3 GG : Nodes, Elements = 13450 61609 AFLR3 GG : Nodes, Elements = 16238 70196 AFLR3 GG : Nodes, Elements = 16238 82337 AFLR3 GG : Nodes, Elements = 16238 78892 AFLR3 GG : Nodes, Elements = 16238 78137 AFLR3 GG : Nodes, Elements = 19188 87158 AFLR3 GG : Nodes, Elements = 19188 99776 AFLR3 GG : Nodes, Elements = 19188 96365 AFLR3 GG : Nodes, Elements = 19188 95572 AFLR3 GG : Nodes, Elements = 22304 105061 AFLR3 GG : Nodes, Elements = 22304 118271 AFLR3 GG : Nodes, Elements = 22304 114811 AFLR3 GG : Nodes, Elements = 22304 114030 AFLR3 GG : Nodes, Elements = 25475 123681 AFLR3 GG : Nodes, Elements = 25475 137067 AFLR3 GG : Nodes, Elements = 25475 133537 AFLR3 GG : Nodes, Elements = 25475 132780 AFLR3 GG : Nodes, Elements = 28675 142487 AFLR3 GG : Nodes, Elements = 28675 156012 AFLR3 GG : Nodes, Elements = 28675 152457 AFLR3 GG : Nodes, Elements = 28675 151739 AFLR3 GG : Nodes, Elements = 31934 161625 AFLR3 GG : Nodes, Elements = 31934 175349 AFLR3 GG : Nodes, Elements = 31934 171839 AFLR3 GG : Nodes, Elements = 31934 171106 AFLR3 GG : Nodes, Elements = 35163 180863 AFLR3 GG : Nodes, Elements = 35163 194576 AFLR3 GG : Nodes, Elements = 35163 190963 AFLR3 GG : Nodes, Elements = 35163 190274 AFLR3 GG : Nodes, Elements = 38336 199857 AFLR3 GG : Nodes, Elements = 38336 213429 AFLR3 GG : Nodes, Elements = 38336 209909 AFLR3 GG : Nodes, Elements = 38336 209231 AFLR3 GG : Nodes, Elements = 41434 218581 AFLR3 GG : Nodes, Elements = 41434 231715 AFLR3 GG : Nodes, Elements = 41434 228240 AFLR3 GG : Nodes, Elements = 41434 227631 AFLR3 GG : Nodes, Elements = 44440 236679 AFLR3 GG : Nodes, Elements = 44440 249363 AFLR3 GG : Nodes, Elements = 44440 246132 AFLR3 GG : Nodes, Elements = 44440 245533 AFLR3 GG : Nodes, Elements = 47347 254281 AFLR3 GG : Nodes, Elements = 47347 266689 AFLR3 GG : Nodes, Elements = 47347 263399 AFLR3 GG : Nodes, Elements = 47347 262800 AFLR3 GG : Nodes, Elements = 50173 271299 AFLR3 GG : Nodes, Elements = 50173 283107 AFLR3 GG : Nodes, Elements = 50173 280170 AFLR3 GG : Nodes, Elements = 50173 279671 AFLR3 GG : Nodes, Elements = 52815 287608 AFLR3 GG : Nodes, Elements = 52815 298804 AFLR3 GG : Nodes, Elements = 52815 295916 AFLR3 GG : Nodes, Elements = 52815 295442 AFLR3 GG : Nodes, Elements = 55304 302914 AFLR3 GG : Nodes, Elements = 55304 313461 AFLR3 GG : Nodes, Elements = 55304 310793 AFLR3 GG : Nodes, Elements = 55304 310363 AFLR3 GG : Nodes, Elements = 57635 317360 AFLR3 GG : Nodes, Elements = 57635 327233 AFLR3 GG : Nodes, Elements = 57635 324637 AFLR3 GG : Nodes, Elements = 57635 324280 AFLR3 GG : Nodes, Elements = 59724 330549 AFLR3 GG : Nodes, Elements = 59724 339298 AFLR3 GG : Nodes, Elements = 59724 337038 AFLR3 GG : Nodes, Elements = 59724 336752 AFLR3 GG : Nodes, Elements = 61562 342268 AFLR3 GG : Nodes, Elements = 61562 349934 AFLR3 GG : Nodes, Elements = 61562 347979 AFLR3 GG : Nodes, Elements = 61562 347773 AFLR3 GG : Nodes, Elements = 63109 352415 AFLR3 GG : Nodes, Elements = 63109 359035 AFLR3 GG : Nodes, Elements = 63109 357272 AFLR3 GG : Nodes, Elements = 63109 357093 AFLR3 GG : Nodes, Elements = 64355 360832 AFLR3 GG : Nodes, Elements = 64355 366080 AFLR3 GG : Nodes, Elements = 64355 364756 AFLR3 GG : Nodes, Elements = 64355 364628 AFLR3 GG : Nodes, Elements = 65290 367433 AFLR3 GG : Nodes, Elements = 65290 371353 AFLR3 GG : Nodes, Elements = 65290 370306 AFLR3 GG : Nodes, Elements = 65290 370196 AFLR3 GG : Nodes, Elements = 65976 372254 AFLR3 GG : Nodes, Elements = 65976 375192 AFLR3 GG : Nodes, Elements = 65976 374355 AFLR3 GG : Nodes, Elements = 65976 374298 AFLR3 GG : Nodes, Elements = 66420 375633 AFLR3 GG : Nodes, Elements = 66420 377500 AFLR3 GG : Nodes, Elements = 66420 376965 AFLR3 GG : Nodes, Elements = 66420 376924 AFLR3 GG : Nodes, Elements = 66661 377647 AFLR3 GG : Nodes, Elements = 66661 378639 AFLR3 GG : Nodes, Elements = 66661 378364 AFLR3 GG : Nodes, Elements = 66661 378356 AFLR3 GG : Nodes, Elements = 66797 378764 AFLR3 GG : Nodes, Elements = 66797 379340 AFLR3 GG : Nodes, Elements = 66797 379179 AFLR3 GG : Nodes, Elements = 66797 379161 AFLR3 GG : Nodes, Elements = 66849 379317 AFLR3 GG : Nodes, Elements = 66849 379528 AFLR3 GG : Nodes, Elements = 66849 379462 AFLR3 GG : Nodes, Elements = 66849 379457 AFLR3 GG : Nodes, Elements = 66871 379523 AFLR3 GG : Nodes, Elements = 66871 379611 AFLR3 GG : Nodes, Elements = 66871 379589 AFLR3 GG : Nodes, Elements = 66871 379590 AFLR3 GG : Nodes, Elements = 66876 379605 AFLR3 GG : Nodes, Elements = 66876 379619 AFLR3 GG : Nodes, Elements = 66876 379616 AFLR3 GG : Nodes, Elements = 66877 379619 AFLR3 GG : Nodes, Elements = 66877 379623 AFLR3 GG : Nodes, Elements = 66877 379622 AFLR3 GG : Nodes, Elements = 66916 379739 AFLR3 GG : Nodes, Elements = 66916 379896 AFLR3 GG : Nodes, Elements = 66916 379848 AFLR3 GG : Nodes, Elements = 66916 379839 AFLR3 GG : Nodes, Elements = 66927 379872 AFLR3 GG : Nodes, Elements = 66927 379912 AFLR3 GG : Nodes, Elements = 66927 379900 AFLR3 GG : Nodes, Elements = 66930 379909 AFLR3 GG : Nodes, Elements = 66930 379922 AFLR3 GG : Nodes, Elements = 66930 379916 AFLR3 GG : Nodes, Elements = 66933 379925 AFLR3 GG : Nodes, Elements = 66933 379935 AFLR3 GG : Nodes, Elements = 66933 379933 AFLR3 GG : Nodes, Elements = 66936 379942 AFLR3 GG : Nodes, Elements = 66936 379954 AFLR3 GG : Nodes, Elements = 66936 379950 AFLR3 GG : Nodes, Elements = 66937 379953 AFLR3 GG : Nodes, Elements = 66937 379956 AFLR3 GG : Nodes, Elements = 66937 379955 AFLR3 : CPU Time = 6.356 seconds AFLR3 QI : QUALITY IMPROVEMENT AFLR3 QI : Nodes, Elements = 66937 379955 AFLR3 QI : Nodes, Elements = 65603 372405 AFLR3 QI : Nodes, Elements = 65393 371215 AFLR3 QI : Nodes, Elements = 65367 371065 AFLR3 QI : Nodes, Elements = 65361 371028 AFLR3 QI : Nodes, Elements = 65360 371022 AFLR3 QI : Nodes, Elements = 65360 374533 AFLR3 QI : Nodes, Elements = 65360 370824 AFLR3 QI : Nodes, Elements = 65360 370404 AFLR3 QI : Nodes, Elements = 65360 372792 AFLR3 QI : Nodes, Elements = 65360 370439 AFLR3 QI : Nodes, Elements = 65360 370349 AFLR3 QI : Nodes, Elements = 65360 372662 AFLR3 QI : Nodes, Elements = 65360 370400 AFLR3 QI : Nodes, Elements = 65360 370340 AFLR3 QI : Nodes, Elements = 65360 372613 AFLR3 QI : Nodes, Elements = 65360 370385 AFLR3 QI : Nodes, Elements = 65360 370331 AFLR3 QI : Nodes, Elements = 65360 372584 AFLR3 QI : Nodes, Elements = 65360 370375 AFLR3 QI : Nodes, Elements = 65360 370325 AFLR3 QI : Nodes, Elements = 65370 370371 AFLR3 QI : Nodes, Elements = 65370 372641 AFLR3 QI : Nodes, Elements = 65370 370426 AFLR3 QI : Nodes, Elements = 65370 370384 AFLR3 QI : Nodes, Elements = 65370 372133 AFLR3 QI : Nodes, Elements = 65370 370386 AFLR3 QI : Nodes, Elements = 65370 370317 AFLR3 QI : Nodes, Elements = 65370 370371 AFLR3 : CPU Time = 3.054 seconds AFLR3 QRG: QUALITY GRID RE-GENERATION AFLR3 QRG: Nodes, Elements = 65370 370371 AFLR3 QRG: Nodes, Elements = 65396 370514 AFLR3 QRG: Nodes, Elements = 65401 370544 AFLR3 QRG: Nodes, Elements = 65401 370543 AFLR3 QRG: Nodes, Elements = 65400 370538 AFLR3 QRG: Nodes, Elements = 65402 370551 AFLR3 : CPU Time = 0.077 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 370551 UG3 : Min, Max Ang = 0.928 177.4 UG3 : Average Angle = 70.1 UG3 : No. Angle>160.0 = 154 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 2.12e+06 UG3 : No. Tet Elems = 370551 UG3 : Min Vol = 6.85e-10 UG3 : Average Vol = 5.73 UG3 : Total-Tet-Vol = 2.12e+06 UG3 : No. Vol160.0 = 154 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 2.12e+06 UG3 : No. Tet Elems = 370551 UG3 : Min Vol = 6.85e-10 UG3 : Average Vol = 5.73 UG3 : Total-Tet-Vol = 2.12e+06 UG3 : No. Vol Edge #9 (9) Internally in Loop 4 7, sen = -1! 110333E00 EGADS Info: Face #3 -> Edge #9 (9) Internally in Loop 7 4, sen = 1! 70000AC77000 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 7 4, sen = -1! 70000AC77000 EGADS Info: Face #5 -> Edge #17 (9) Internally in Loop 4 7, sen = 1! Getting surface mesh for body 7 (of 7) Body 1 (of 7) Number of nodes = 98 Number of elements = 192 Number of triangle elements = 192 Number of quadrilateral elements = 0 Body 2 (of 7) Number of nodes = 294 Number of elements = 584 Number of triangle elements = 584 Number of quadrilateral elements = 0 Body 3 (of 7) Number of nodes = 488 Number of elements = 972 Number of triangle elements = 972 Number of quadrilateral elements = 0 Body 4 (of 7) Number of nodes = 2048 Number of elements = 4096 Number of triangle elements = 4096 Number of quadrilateral elements = 0 Body 5 (of 7) Number of nodes = 152 Number of elements = 300 Number of triangle elements = 300 Number of quadrilateral elements = 0 Body 6 (of 7) Number of nodes = 624 Number of elements = 1248 Number of triangle elements = 1248 Number of quadrilateral elements = 0 Body 7 (of 7) Number of nodes = 488 Number of elements = 972 Number of triangle elements = 972 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 4192 Total number of elements = 8364 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Body 1 number of surface: nodes - 98, elements - 192 Body 2 number of surface: nodes - 294, elements - 584 Body 3 number of surface: nodes - 488, elements - 972 Body 4 number of surface: nodes - 2048, elements - 4096 Body 5 number of surface: nodes - 152, elements - 300 Body 6 number of surface: nodes - 624, elements - 1248 Body 7 number of surface: nodes - 488, elements - 972 Getting volume mesh for body 1 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = box, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = cylinder, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 3 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = cone, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 4 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = torus, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 5 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = sphere, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 6 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = boxhole, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 7 (of 7) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = bullet, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Body 1 number of surface: nodes - 98, elements - 192 Body 2 number of surface: nodes - 294, elements - 584 Body 3 number of surface: nodes - 488, elements - 972 Body 4 number of surface: nodes - 2048, elements - 4096 Body 5 number of surface: nodes - 152, elements - 300 Body 6 number of surface: nodes - 624, elements - 1248 Body 7 number of surface: nodes - 488, elements - 972 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = box, index = 1 Name = cylinder, index = 2 Name = cone, index = 3 Name = torus, index = 4 Name = sphere, index = 5 Name = boxhole, index = 6 Name = bullet, index = 7 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Number of surface: nodes - 4192, elements - 8364 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ok test_faceMatch_MultiDomain (test_tetgen.TestTETGEN.test_faceMatch_MultiDomain) ... ../csmData/MultiDomain/example1.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 374 Number of elements = 744 Number of triangle elements = 744 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 98 Number of elements = 192 Number of triangle elements = 192 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 472 Total number of elements = 936 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 374, elements - 744 Body 2 number of surface: nodes - 98, elements - 192 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 374, elements - 744 Body 2 number of surface: nodes - 98, elements - 192 Getting volume mesh for body 1 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ../csmData/MultiDomain/example2.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 386 Number of elements = 768 Number of triangle elements = 768 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 98 Number of elements = 192 Number of triangle elements = 192 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 98 Number of elements = 192 Number of triangle elements = 192 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 582 Total number of elements = 1152 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 386, elements - 768 Body 2 number of surface: nodes - 98, elements - 192 Body 3 number of surface: nodes - 98, elements - 192 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 386, elements - 768 Body 2 number of surface: nodes - 98, elements - 192 Body 3 number of surface: nodes - 98, elements - 192 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ../csmData/MultiDomain/example3.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 351 Number of elements = 698 Number of triangle elements = 698 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 98 Number of elements = 192 Number of triangle elements = 192 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 42 Number of elements = 80 Number of triangle elements = 80 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 491 Total number of elements = 970 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 351, elements - 698 Body 2 number of surface: nodes - 98, elements - 192 Body 3 number of surface: nodes - 42, elements - 80 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 351, elements - 698 Body 2 number of surface: nodes - 98, elements - 192 Body 3 number of surface: nodes - 42, elements - 80 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ../csmData/MultiDomain/example4.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 376 Number of elements = 748 Number of triangle elements = 748 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 98 Number of elements = 192 Number of triangle elements = 192 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 42 Number of elements = 80 Number of triangle elements = 80 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 516 Total number of elements = 1020 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 376, elements - 748 Body 2 number of surface: nodes - 98, elements - 192 Body 3 number of surface: nodes - 42, elements - 80 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 376, elements - 748 Body 2 number of surface: nodes - 98, elements - 192 Body 3 number of surface: nodes - 42, elements - 80 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ../csmData/MultiDomain/example6.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 370 Number of elements = 736 Number of triangle elements = 736 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 42 Number of elements = 80 Number of triangle elements = 80 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 42 Number of elements = 80 Number of triangle elements = 80 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 454 Total number of elements = 896 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 370, elements - 736 Body 2 number of surface: nodes - 42, elements - 80 Body 3 number of surface: nodes - 42, elements - 80 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 370, elements - 736 Body 2 number of surface: nodes - 42, elements - 80 Body 3 number of surface: nodes - 42, elements - 80 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ../csmData/MultiDomain/example7.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 370 Number of elements = 736 Number of triangle elements = 736 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 126 Number of elements = 252 Number of triangle elements = 252 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 20 Number of elements = 36 Number of triangle elements = 36 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 516 Total number of elements = 1024 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 370, elements - 736 Body 2 number of surface: nodes - 126, elements - 252 Body 3 number of surface: nodes - 20, elements - 36 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 370, elements - 736 Body 2 number of surface: nodes - 126, elements - 252 Body 3 number of surface: nodes - 20, elements - 36 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ../csmData/MultiDomain/example8.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 109 Number of elements = 214 Number of triangle elements = 214 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 48 Number of elements = 96 Number of triangle elements = 96 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 12 Number of elements = 20 Number of triangle elements = 20 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 169 Total number of elements = 330 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 109, elements - 214 Body 2 number of surface: nodes - 48, elements - 96 Body 3 number of surface: nodes - 12, elements - 20 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 109, elements - 214 Body 2 number of surface: nodes - 48, elements - 96 Body 3 number of surface: nodes - 12, elements - 20 Getting volume mesh for body 1 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 3 (of 3) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ../csmData/MultiDomain/example9.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 536 Number of elements = 1072 Number of triangle elements = 1072 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 544 Number of elements = 1084 Number of triangle elements = 1084 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 1080 Total number of elements = 2156 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 536, elements - 1072 Body 2 number of surface: nodes - 544, elements - 1084 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 536, elements - 1072 Body 2 number of surface: nodes - 544, elements - 1084 Getting volume mesh for body 1 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ../csmData/MultiDomain/multi_prim.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 5) Getting surface mesh for body 2 (of 5) Getting surface mesh for body 3 (of 5) Getting surface mesh for body 4 (of 5) Getting surface mesh for body 5 (of 5) Body 1 (of 5) Number of nodes = 1351 Number of elements = 2682 Number of triangle elements = 2682 Number of quadrilateral elements = 0 Body 2 (of 5) Number of nodes = 288 Number of elements = 572 Number of triangle elements = 572 Number of quadrilateral elements = 0 Body 3 (of 5) Number of nodes = 174 Number of elements = 344 Number of triangle elements = 344 Number of quadrilateral elements = 0 Body 4 (of 5) Number of nodes = 26 Number of elements = 48 Number of triangle elements = 48 Number of quadrilateral elements = 0 Body 5 (of 5) Number of nodes = 482 Number of elements = 960 Number of triangle elements = 960 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 2321 Total number of elements = 4606 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 1351, elements - 2682 Body 2 number of surface: nodes - 288, elements - 572 Body 3 number of surface: nodes - 174, elements - 344 Body 4 number of surface: nodes - 26, elements - 48 Body 5 number of surface: nodes - 482, elements - 960 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 1351, elements - 2682 Body 2 number of surface: nodes - 288, elements - 572 Body 3 number of surface: nodes - 174, elements - 344 Body 4 number of surface: nodes - 26, elements - 48 Body 5 number of surface: nodes - 482, elements - 960 Getting volume mesh for body 1 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 3 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 4 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 5 (of 5) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ../csmData/MultiDomain/cyl_seam.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 444 Number of elements = 884 Number of triangle elements = 884 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 522 Number of elements = 1044 Number of triangle elements = 1044 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 966 Total number of elements = 1928 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 444, elements - 884 Body 2 number of surface: nodes - 522, elements - 1044 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Body 1 number of surface: nodes - 444, elements - 884 Body 2 number of surface: nodes - 522, elements - 1044 Getting volume mesh for body 1 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Getting volume mesh for body 2 (of 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = dummy_att, index = 1 Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ok test_journal (test_tetgen.TestTETGEN.test_journal) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Number of surface: nodes - 7173, elements - 14338 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Number of surface: nodes - 7173, elements - 14338 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq2.000/0.000QT1.00e-16A Done meshing using TetGen! EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Number of surface: nodes - 7173, elements - 14338 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 CAPS Info: Hit last success -- going live! CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Number of surface: nodes - 7173, elements - 14338 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq2.000/0.000QT1.00e-16A Done meshing using TetGen! CAPS Info: Hit last success -- going live! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 ok test_phase (test_tetgen.TestTETGEN.test_phase) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Number of surface: nodes - 7173, elements - 14338 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Number of surface: nodes - 5924, elements - 11840 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! ok test_reenter (test_tetgen.TestTETGEN.test_reenter) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = riteWing, index = 2 Name = leftWing, index = 3 Name = trailingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 7173 Number of elements = 14338 Number of triangle elements = 14338 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 7173 Total number of elements = 14338 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Number of surface: nodes - 7173, elements - 14338 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Farfield, index = 1 Name = Wing1, index = 2 Number of surface: nodes - 7173, elements - 14338 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq2.000/0.000QT1.00e-16A Done meshing using TetGen! Writing Binary VTK file .... Finished writing Binary VTK file Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing FAST file .... Finished writing FAST file Writing SU2 file .... Finished writing SU2 file Writing Binary STL file .... Finished writing Binary STL file Writing ASCII STL file .... Finished writing ASCII STL file Writing Tecplot file .... Finished writing Tecplot file ok test_setInput (test_tetgen.TestTETGEN.test_setInput) ... EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! ok test_Cl (test_xfoil.Testxfoil_Kulfan.test_Cl) ... ok test_alpha_custom_increment (test_xfoil.Testxfoil_Kulfan.test_alpha_custom_increment) ... ok test_CL_uniform_increment (test_xfoil.Testxfoil_NACA.test_CL_uniform_increment) ... ok test_Cl (test_xfoil.Testxfoil_NACA.test_Cl) ... ok test_alpha_custom_increment (test_xfoil.Testxfoil_NACA.test_alpha_custom_increment) ... ok test_alpha_uniform_inrement (test_xfoil.Testxfoil_NACA.test_alpha_uniform_inrement) ... ok test_append (test_xfoil.Testxfoil_NACA.test_append) ... ok test_normalize (test_xfoil.Testxfoil_NACA.test_normalize) ... ok test_phase (test_xfoil.Testxfoil_NACA.test_phase) ... ok test_Cl (test_xfoil.Testxfoil_Parsec.test_Cl) ... ok test_alpha_custom_increment (test_xfoil.Testxfoil_Parsec.test_alpha_custom_increment) ... ok test_Output (test_zaero.TestZAERO.test_Output) ... ok test_inputs (test_zaero.TestZAERO.test_inputs) ... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = Ribs, index = 1 Name = Skin, index = 2 Name = Spar1, index = 3 Name = Rib_Root, index = 4 Name = Spar2, index = 5 Name = Rib_Root_Point, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = LeadingEdge, index = 1 Name = TrailingEdge, index = 2 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 1220 Number of elements = 2680 Number of triangle elements = 2680 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 1 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 1221 Total number of elements = 2680 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root_Point, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = Skin_Top, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = Rib_Root, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = Ribs, index = 1 Name = Skin, index = 2 Name = Spar1, index = 3 Name = Rib_Root, index = 4 Name = Spar2, index = 5 Name = Rib_Root_Point, index = 6 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1220 Number of elements = 2680 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 2680 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 1221 Combined Number of elements = 2681 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 2680 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 6 Property name - Rib_Root Property name - Rib_Root_Point Property name - Ribs Property name - Skin Property name - Spar1 Property name - Spar2 Done getting FEA properties Updating mesh element types based on properties input 'Smart_Restart' is ON Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Getting vortex lattice surface data VLM surface name - WingSurface Done getting vortex lattice surface data Getting vortex lattice control surface data VLM control surface name - CntrlLE VLM control surface name - CntrlTE Done getting vortex lattice control surface data Getting FEA vortex lattice mesh Getting ZAERO UAIC Configurations....... Number of UAIC Configurations - 2 UAIC Configuration: climb, id = 1 - Mach Number : 0.200000 - Reduced Freq: [0.020000, ... , 0.250000] UAIC Configuration: cruise, id = 2 - Mach Number : 0.700000 - Reduced Freq: [0.040000, ... , 0.350000] Getting ZAERO Analysis Subcases....... Number of Analysis Subcases - 2 Analysis Subcase: FlutterCruise, id = 1 - Discipline : flutter - UAIC : cruise Analysis Subcase: Trim, id = 2 - Discipline : Trim - UAIC : climb Getting ZAERO Trim Variables....... Number of Trim Variables - 2 Trim Variable: ANGLEA - Label : ALPHA - Value : free Trim Variable: URDD3 - Label : NZ - Value : 1.0 Updating StaticAeroelastic subcase: Trim - vectorToCG -> [0.345898, 1.652951, -0.041403] - weight -> 476456.149985 - weightMomentOfInertia -> [304902.643270, 98963.803820, 69822.813290, 6179.981375, 19723.152207, 370546.335523] ok ---------------------------------------------------------------------- Ran 154 tests in 951.081s OK (skipped=15) + cd /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest + ./execute_CTestRegression.sh No options provided...defaulting to ALL Running.... MINIMAL c-Tests Running.... LINEARAERO c-Tests ================================================= + echo './avlTest test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt ./avlTest test; + ./avlTest 0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt Attention: avlTest is hard coded to look for ../csmData/avlWingTail.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice control surface data VLM control surface name - WingRightLE VLM control surface name - WingRightTE VLM control surface name - Tail Done getting vortex lattice control surface data Getting vortex lattice surface data VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Wing (ID = 0) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Writing surface - Vertical_Tail (ID = 1) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Running AVL! Value of Cltot = 0.619913 StripForces Wing = 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Vertical_Tail = {"Xle":[5.481142821257e+00,5.457739875756e+00,5.413224828118e+00,5.351955121359e+00,5.279928261269e+00,5.204194738752e+00,5.132167878660e+00,5.070898171897e+00,5.026383124254e+00,5.002980178746e+00],"Yle":[0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00],"Zle":[1.462285642514e+00,1.415479751513e+00,1.326449656236e+00,1.203910242719e+00,1.059856522538e+00,9.083894775049e-01,7.643357573198e-01,6.417963437947e-01,5.527662485071e-01,5.059603574925e-01],"Chord":[7.291641787429e-01,7.525671242437e-01,7.970821718820e-01,8.583518786405e-01,9.303787387310e-01,1.006112261248e+00,1.078139121340e+00,1.139408828103e+00,1.183923875746e+00,1.207326821254e+00],"Area":[1.727730179136e-02,5.174997687051e-02,8.537019049526e-02,1.158415604078e-01,1.391867381176e-01,1.505166423044e-01,1.455036346588e-01,1.220345306258e-01,8.141205112924e-02,2.860720599220e-02],"c_cl":[4.143502484418e-02,1.146121890397e-01,1.669674480704e-01,2.000258625574e-01,2.165069436647e-01,2.173612378313e-01,2.020982864238e-01,1.687203348324e-01,1.143884794128e-01,4.073751989356e-02],"ai":[2.065296924524e-01,1.849180223915e-01,1.591285664757e-01,1.456224964407e-01,1.435231644006e-01,1.506386553619e-01,1.666466052405e-01,1.914179167692e-01,2.193221173426e-01,2.365321328628e-01],"cl_norm":[6.579957348175e-02,1.763463053600e-01,2.425545992661e-01,2.698370559984e-01,2.694590983036e-01,2.501591871286e-01,2.170544160378e-01,1.714623014102e-01,1.118766125248e-01,3.907064104103e-02],"cl":[5.682537081788e-02,1.522949719002e-01,2.094733190132e-01,2.330348048801e-01,2.327083956798e-01,2.160407403860e-01,1.874510278160e-01,1.480770823176e-01,9.661810337317e-02,3.374191575671e-02],"cd":[4.670566079259e-03,1.374698956983e-02,1.845844898550e-02,2.032218684722e-02,2.072187092669e-02,2.023884851594e-02,1.896705322928e-02,1.657142171116e-02,1.222733795464e-02,5.106244760906e-03],"cdv":[0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00,0.000000000000e+00],"cm_c/4":[-3.303465544546e-02,-8.761746958841e-02,-1.194746602282e-01,-1.341488123562e-01,-1.380350789961e-01,-1.339349413679e-01,-1.218867053323e-01,-1.002593790934e-01,-6.716156843018e-02,-2.373448304332e-02],"cm_LE":[-4.232877133358e-02,-1.126299441676e-01,-1.539951982649e-01,-1.724118490115e-01,-1.757829360722e-01,-1.683239687782e-01,-1.510824211715e-01,-1.228726806386e-01,-8.171902803714e-02,-2.878672165371e-02],"C.P.x/c":[8.313363814436e-01,8.253142634666e-01,8.203574125382e-01,8.256599853196e-01,8.431675932571e-01,8.699522420103e-01,9.002322593393e-01,9.270755982235e-01,9.451240614896e-01,9.534124326092e-01]} real 0m0.719s user 0m0.401s sys 0m0.211s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./avlTest passed (as expected) ============================================= ================================================= + echo './msesTest test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt ./msesTest test; + ./msesTest 0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt Attention: msesTest is hard coded to look for ../csmData/airfoilSection.csm Value of CL = 0.276892 real 0m2.056s user 0m1.833s sys 0m0.146s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./msesTest passed (as expected) ============================================= ================================================= + echo './frictionTest test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt ./frictionTest test; + ./frictionTest 0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt Attention: frictionTest is hard coded to look for ../csmData/frictionWingTailFuselage.csm To not make system calls to the friction executable the second command line option may be supplied - 0 = no analysis , >0 run analysis (default). Lifting Surface: Body = 1, units m XLE: 1.571946 -3.872983 0.249728 XTE: 2.536563 -3.872983 0.335335 Chord: 0.968408 Arc: 1.985181 T/C: 0.155975 Type: Wing Lifting Surface: Body = 2, units m XLE: 0.000000 0.000000 0.000000 XTE: 1.614012 0.000000 0.002015 Chord: 1.614013 Arc: 3.308635 T/C: 0.127839 Type: Wing Lifting Surface: Body = 3, units m XLE: 1.571946 3.872983 0.249728 XTE: 2.536563 3.872983 0.335335 Chord: 0.968408 Arc: 1.985181 T/C: 0.155975 Type: Wing Lifting Surface: Body = 4, units m XLE: 5.484123 0.000000 1.468246 XTE: 6.210307 0.000915 1.468246 Chord: 0.726185 Arc: 1.482717 T/C: 0.120035 Type: VTail Lifting Surface: Body = 5, units m XLE: 5.000000 0.000000 0.500000 XTE: 6.210307 0.001525 0.500000 Chord: 1.210308 Arc: 2.471195 T/C: 0.120035 Type: VTail Lifting Surface: Body = 6, units m XLE: 5.484123 -0.968246 0.500000 XTE: 6.210307 -0.968246 0.500915 Chord: 0.726185 Arc: 1.482717 T/C: 0.120035 Type: HTail Lifting Surface: Body = 7, units m XLE: 5.484123 0.968246 0.500000 XTE: 6.210307 0.968246 0.500915 Chord: 0.726185 Arc: 1.482717 T/C: 0.120035 Type: HTail Body of Revolution: Body = 8, units m Arc: 0.000000 Diameter: 0.000000 Type: Fuse Body of Revolution: Body = 9, units m Arc: 3.714180 Diameter: 1.020621 Type: Fuse Body of Revolution: Body = 10, units m Arc: 2.771209 Diameter: 0.645497 Type: Fuse Body of Revolution: Body = 11, units m Arc: 1.013945 Diameter: 0.322749 Type: Fuse Body of Revolution: Body = 12, units m Arc: 0.101394 Diameter: 0.032275 Type: Fuse Number of sections 4, number of revolution sections 1 Number of Mach-Altitude cases = 2 Running FRICTION! Value of CDfric = 0.009900 Value of CDfric = 0.009190 real 0m0.514s user 0m0.138s sys 0m0.067s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./frictionTest passed (as expected) ============================================= Running.... MESH c-Tests Running.... CFD c-Tests ================================================= + echo './fun3dAFLR2Test test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt ./fun3dAFLR2Test test; + ./fun3dAFLR2Test 0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt Attention: fun3dAFLR2Test is hard coded to look for ../csmData/cfd2D.csm Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting 2D mesh for body 1 (of 1) UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mquad = 1 UG PARAM : mpp = 3 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 841 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 841 841 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 168 338 AFLR2 IG : Nodes, Faces = 336 674 AFLR2 IG : Nodes, Faces = 504 1010 AFLR2 IG : Nodes, Faces = 617 1236 AFLR2 IG : Nodes, Faces = 672 1346 AFLR2 IG : Nodes, Faces = 741 1484 AFLR2 IG : Nodes, Faces = 803 1608 AFLR2 IG : Nodes, Faces = 840 1682 AFLR2 IG : Nodes, Faces = 841 1684 AFLR2 IG : Nodes, Faces = 845 1684 AFLR2 IG : Nodes, Faces = 841 841 AFLR2 : CPU Time = 0.006 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GGp: Nodes, Faces = 841 841 AFLR2 GGp: Nodes, Faces = 1648 2455 AFLR2 GGp: Nodes, Faces = 2446 4051 AFLR2 GGp: Nodes, Faces = 3257 5673 AFLR2 GGp: Nodes, Faces = 4054 7267 AFLR2 GGp: Nodes, Faces = 4821 8801 AFLR2 GGp: Nodes, Faces = 5577 10313 AFLR2 GGp: Nodes, Faces = 6325 11809 AFLR2 GGp: Nodes, Faces = 7053 13265 AFLR2 GGp: Nodes, Faces = 7732 14623 AFLR2 GGp: Nodes, Faces = 8394 15947 AFLR2 GGp: Nodes, Faces = 9022 17203 AFLR2 GGp: Nodes, Faces = 9620 18399 AFLR2 GGp: Nodes, Faces = 10176 19511 AFLR2 GGp: Nodes, Faces = 10689 20537 AFLR2 GGp: Nodes, Faces = 11181 21521 AFLR2 GGp: Nodes, Faces = 11646 22451 AFLR2 GGp: Nodes, Faces = 12098 23355 AFLR2 GGp: Nodes, Faces = 12529 24217 AFLR2 GGp: Nodes, Faces = 12943 25045 AFLR2 GGp: Nodes, Faces = 13331 25821 AFLR2 GGp: Nodes, Faces = 13710 26579 AFLR2 GGp: Nodes, Faces = 14061 27281 AFLR2 GGp: Nodes, Faces = 14424 28007 AFLR2 GGp: Nodes, Faces = 14774 28707 AFLR2 GGp: Nodes, Faces = 15107 29373 AFLR2 GGp: Nodes, Faces = 15422 30003 AFLR2 GGp: Nodes, Faces = 15707 30573 AFLR2 GGp: Nodes, Faces = 15982 31123 AFLR2 GGp: Nodes, Faces = 16233 31625 AFLR2 GGp: Nodes, Faces = 16473 32105 AFLR2 GGp: Nodes, Faces = 16685 32529 AFLR2 GGp: Nodes, Faces = 16898 32955 AFLR2 GGp: Nodes, Faces = 17104 33367 AFLR2 GGp: Nodes, Faces = 17291 33741 AFLR2 GGp: Nodes, Faces = 17468 34095 AFLR2 GGp: Nodes, Faces = 17627 34413 AFLR2 GGp: Nodes, Faces = 17781 34721 AFLR2 GGp: Nodes, Faces = 17929 35017 AFLR2 GGp: Nodes, Faces = 18060 35279 AFLR2 GGp: Nodes, Faces = 18186 35531 AFLR2 GGp: Nodes, Faces = 18292 35743 AFLR2 GGp: Nodes, Faces = 18403 35965 AFLR2 GGp: Nodes, Faces = 18499 36157 AFLR2 GGp: Nodes, Faces = 18568 36295 AFLR2 GGp: Nodes, Faces = 18603 36365 AFLR2 GGp: Nodes, Faces = 18615 36389 AFLR2 : CPU Time = 0.077 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 18615 36389 AFLR2 QI : Nodes, Faces = 18608 1893 AFLR2 QI : Nodes, Faces = 18608 17241 AFLR2 QI : Nodes, Faces = 18608 36375 AFLR2 QI : Nodes, Faces = 18606 1789 AFLR2 QI : Nodes, Faces = 18606 17291 AFLR2 QI : Nodes, Faces = 18606 36371 AFLR2 QI : Nodes, Faces = 18604 1971 AFLR2 QI : Nodes, Faces = 18604 17198 AFLR2 QI : Nodes, Faces = 18604 36367 AFLR2 QI : Nodes, Faces = 18604 2161 AFLR2 QI : Nodes, Faces = 18604 17103 AFLR2 QI : Nodes, Faces = 18604 36367 AFLR2 QI : Nodes, Faces = 18604 2149 AFLR2 QI : Nodes, Faces = 18604 17109 AFLR2 QI : Nodes, Faces = 18604 2149 AFLR2 QI : Nodes, Faces = 18604 17109 AFLR2 : CPU Time = 0.037 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 18604 Number of elements = 20099 Number of tris = 2149 Number of quad = 17109 Writing Tecplot file .... Tecplot expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing Tecplot file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - TunnelWall Boundary condition name - InFlow Boundary condition name - OutFlow Done getting CFD boundary conditions Python library was linked, but will not be used! Creating a 3D volume mesh from a 2D surface Number of Nodes = 37208 Number of Prisms = 2149 Number of Hexahedral = 17109 Writing AFLR3 file .... Finished writing AFLR3 file Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. NOT Running fun3d! real 0m1.321s user 0m1.132s sys 0m0.327s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./fun3dAFLR2Test passed (as expected) ============================================= ================================================= + echo './fun3dTetgenTest test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt ./fun3dTetgenTest test; + ./fun3dTetgenTest 0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt Attention: fun3dTetgenTest is hard coded to look for ../csmData/cfdMultiBody.csm Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 9618 Number of elements = 19232 Number of triangle elements = 19232 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 6142 Number of elements = 12280 Number of triangle elements = 12280 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 267 Number of elements = 530 Number of triangle elements = 530 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 16027 Total number of elements = 32042 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 16027, elements - 32042 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.185406 Creating surface mesh ... Surface mesh seconds: 0.046354 Recovering boundaries... Boundary recovery seconds: 0.150763 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.059195 Recovering Delaunayness... Delaunay recovery seconds: 0.082325 Refining mesh... 21363 insertions, added 16942 points, 799712 tetrahedra in queue. 7113 insertions, added 2754 points, 343153 tetrahedra in queue. Refinement seconds: 2.27313 Smoothing vertices... Mesh smoothing seconds: 2.94536 Improving mesh... Mesh improvement seconds: 0.071305 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.030612 Total running seconds: 5.84557 Statistics: Input points: 16027 Input facets: 32042 Input segments: 48063 Input holes: 2 Input regions: 0 Mesh points: 37108 Mesh tetrahedra: 179009 Mesh faces: 374039 Mesh faces on exterior boundary: 32042 Mesh faces on input facets: 32042 Mesh edges on input segments: 48063 Steiner points inside domain: 21081 Done meshing using TetGen! Getting CFD boundary conditions Boundary condition name - Wing1 Boundary condition name - Wing2 Boundary condition name - Farfield Done getting CFD boundary conditions Python library was linked, but will not be used! Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. NOT Running fun3d! real 0m9.490s user 0m10.066s sys 0m0.564s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./fun3dTetgenTest passed (as expected) ============================================= Running.... STRUCTURE c-Tests ================================================= + echo './interferenceTest test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt ./interferenceTest test; + ./interferenceTest + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt Note: interferenceTest uses ../csmData/interference.csm classifyClouds: EG_generalBoolean = -7! classifyClouds: EG_generalBoolean = -7! classifyClouds: EG_generalBoolean = -7! classifyClouds: EG_generalBoolean = -7! 1: 1.000000e+00 Box 2: 5.849417e-01 Sphere 3: 7.191810e-01 Cylinder 4: 4.000000e+01 OuterBox 0.000000e+00 -2.685383e-02 0.000000e+00 0.000000e+00 -2.685383e-02 0.000000e+00 0.000000e+00 -2.592150e-02 0.000000e+00 0.000000e+00 0.000000e+00 0.000000e+00 0.000000e+00 -2.592150e-02 0.000000e+00 1.000000e+00 classifyClouds: EG_generalBoolean = -7! classifyClouds: EG_generalBoolean = -7! 1: 1.000000e+00 Box 2: 5.886880e-01 Sphere 3: 7.235323e-01 Cylinder 0.000000e+00 -2.035193e-02 0.000000e+00 -2.035193e-02 0.000000e+00 0.000000e+00 0.000000e+00 0.000000e+00 0.000000e+00 real 0m3.600s user 0m6.378s sys 0m0.154s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./interferenceTest passed (as expected) ============================================= ================================================= + echo './hsmCantileverPlateTest test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt ./hsmCantileverPlateTest test; + ./hsmCantileverPlateTest 0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt Attention: hsmCantileverPlate is hard coded to look for ../csmData/feaJoinedPlate.csm Mapping Csys attributes ................ Number of unique Csys attributes = 1 Name = plate, index = 1 Getting FEA coordinate systems....... Number of coordinate systems - 1 Coordinate system name - plate Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plateTip, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Creating HSM BEM Getting quads for BEM! Number of nodal coordinates = 40 Number of elements = 51 Elemental Tria3 = 0 Elemental Quad4 = 27 Getting FEA materials....... Number of materials - 1 Material name - Madeupium No "materialType" specified for Material tuple Madeupium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate No "material" specified for Property tuple plate, defaulting to an index of 1 Done getting FEA properties Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA loads....... Number of loads - 1 Load name - appliedLoad Done getting FEA loads Writing Nastran grid and connectivity file (in small field format) .... Finished writing Nastran grid file Max Adjacency set to = 9 MaxDim = 4, numBCEdge = 3, numBCNode = 4, numJoint = 0 NEED TO ADD MORE CODE TO hsm_setGlobalParameter NEED TO ADD MORE CODE TO hsm_setNodeBCParameter NumBCNode = 4 ->HSMSOL Matrix Non-zero Entries = 1313 Converging HSM equation system ... iter dr dd dp rlx max 1 0.314E+01 0.628E+01 0.000E+00 0.080 ddx @ ( 1.00 0.00 0.00) 1* 0.341E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 1* 0.326E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 1* 0.438E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 2 0.274E+01 0.521E+01 0.106E-07 0.096 ddx @ ( 1.00 0.07 0.00) 2* 0.321E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 2* 0.373E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.03 0.00) 2* 0.777E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.03 0.00) 3 0.202E+01 0.439E+01 0.928E-07 0.114 ddz @ ( 1.00 0.03 0.00) 3* 0.442E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.07 0.00) 3* 0.623E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.07 0.00) 3* 0.163E-03 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.07 0.00) 3* 0.167E-06 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 4 0.192E+01 0.476E+01 0.126E-07 0.105 ddz @ ( 1.00 0.03 0.00) 4* 0.335E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 4* 0.332E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 4* 0.451E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 5 0.187E+01 0.394E+01 0.254E-07 0.127 ddz @ ( 1.00 0.07 0.00) 5* 0.353E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 5* 0.379E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 5* 0.638E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 6 0.156E+01 0.300E+01 0.112E-06 0.166 ddx @ ( 1.00 0.03 0.00) 6* 0.326E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 6* 0.575E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 6* 0.193E-03 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 6* 0.272E-06 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 7 0.103E+01 0.323E+01 0.345E-07 0.155 ddx @ ( 1.00 0.07 0.00) 7* 0.259E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 7* 0.297E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 7* 0.435E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 8 0.756E+00 0.259E+01 0.139E-07 0.193 ddx @ ( 1.00 0.03 0.00) 8* 0.295E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 8* 0.350E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 8* 0.587E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 9 0.678E+00 0.179E+01 0.639E-07 0.279 ddx @ ( 0.89 0.10 0.00) 9* 0.330E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 9* 0.457E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 9* 0.167E-03 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 9* 0.264E-06 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 10 0.452E+00 0.171E+01 0.499E-07 0.292 ddz @ ( 1.00 0.10 0.00) 10* 0.166E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 10* 0.239E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 10* 0.393E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) iter dr dd dp rlx max 11 0.257E+00 0.120E+01 0.614E-08 0.417 ddz @ ( 1.00 0.10 0.00) 11* 0.206E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 11* 0.283E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 11* 0.488E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 12 0.131E+00 0.647E+00 0.288E-08 0.772 ddz @ ( 0.89 0.10 0.00) 12* 0.238E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 12* 0.357E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 12* 0.849E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 13 0.393E-01 0.238E+00 0.325E-07 1.000 ddx @ ( 1.00 0.03 0.00) 13* 0.335E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 13* 0.936E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 14 0.475E-03 0.514E-02 0.635E-07 1.000 ddx @ ( 1.00 0.00 0.00) 15 0.893E-06 0.651E-06 0.135E-08 1.000 drx @ ( 1.00 0.00 0.00) 16 0.573E-10 0.216E-09 0.140E-11 1.000 ddx @ ( 0.44 0.10 0.00) 17 0.179E-15 0.693E-15 0.745E-15 1.000 dps @ ( 0.78 0.00 0.00) Converging n vectors ... it = 1 dn = 0.193E+01 rlx = 1.000 ( 9 ) it = 2 dn = 0.516E-15 rlx = 1.000 ( 13 ) Converging e1,e2 vectors ... it = 1 de = 0.285E+01 rlx = 0.351 ( 24 ) it = 2 de = 0.269E+01 rlx = 0.372 ( 37 ) it = 3 de = 0.249E+01 rlx = 0.402 ( 21 ) it = 4 de = 0.179E+01 rlx = 0.559 ( 21 ) it = 5 de = 0.954E+00 rlx = 1.000 ( 21 ) it = 6 de = 0.152E+00 rlx = 1.000 ( 21 ) it = 7 de = 0.887E-03 rlx = 1.000 ( 21 ) it = 8 de = 0.177E-09 rlx = 1.000 ( 21 ) it = 9 de = 0.876E-16 rlx = 1.000 ( 28 ) Calculating strains, stress resultants ... Writing HSM solution to Tecplot File - hsm_CAPS.dat real 0m0.592s user 0m0.342s sys 0m0.071s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./hsmCantileverPlateTest passed (as expected) ============================================= ================================================= + echo './hsmSimplePlateTest test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt ./hsmSimplePlateTest test; + ./hsmSimplePlateTest 0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt Attention: hsmTest2 is hard coded to look for ../csmData/feaSimplePlate.csm Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plate, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Creating HSM BEM Number of nodal coordinates = 100 Number of elements = 198 Elemental Tria3 = 162 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Madeupium No "materialType" specified for Material tuple Madeupium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate No "material" specified for Property tuple plate, defaulting to an index of 1 Done getting FEA properties Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA loads....... Number of loads - 1 Load name - appliedLoad Done getting FEA loads Writing Nastran grid and connectivity file (in small field format) .... Finished writing Nastran grid file Max Adjacency set to = 7 MaxDim = 36, numBCEdge = 0, numBCNode = 36, numJoint = 0 NEED TO ADD MORE CODE TO hsm_setGlobalParameter NEED TO ADD MORE CODE TO hsm_setNodeBCParameter NumBCNode = 36 ->HSMSOL Matrix Non-zero Entries = 8026 Converging HSM equation system ... iter dr dd dp rlx max 1 0.609E+00 0.519E+01 0.260E+01 0.096 ddy @ ( 0.28 0.25 0.00) 1* 0.571E-01 0.000E+00 0.000E+00 1.000 drz @ ( 0.17 0.11 0.00) 1* 0.159E-01 0.000E+00 0.000E+00 1.000 drz @ ( 0.17 0.11 0.00) 1* 0.254E-02 0.000E+00 0.000E+00 1.000 drz @ ( 0.11 0.14 0.00) 1* 0.838E-04 0.000E+00 0.000E+00 1.000 drz @ ( 0.06 0.14 0.00) 2 0.768E-02 0.754E+00 0.102E+01 0.492 dps @ ( 0.00 0.00 0.00) 2* 0.336E-03 0.000E+00 0.000E+00 1.000 drx @ ( 0.06 0.06 0.00) 2* 0.690E-06 0.000E+00 0.000E+00 1.000 drz @ ( 0.06 0.08 0.00) 3 0.252E-02 0.204E+00 0.299E+00 1.000 dps @ ( 0.50 0.03 0.00) 3* 0.181E-03 0.000E+00 0.000E+00 1.000 drz @ ( 0.39 0.11 0.00) 3* 0.675E-06 0.000E+00 0.000E+00 1.000 drx @ ( 0.44 0.03 0.00) 4 0.108E-03 0.157E-01 0.567E-01 1.000 dps @ ( 0.39 0.14 0.00) 4* 0.249E-05 0.000E+00 0.000E+00 1.000 drx @ ( 0.44 0.22 0.00) 5 0.103E-05 0.374E-03 0.159E-02 1.000 dps @ ( 0.06 0.06 0.00) 6 0.139E-08 0.994E-07 0.421E-06 1.000 dps @ ( 0.50 0.00 0.00) 7 0.106E-15 0.467E-13 0.133E-12 1.000 dps @ ( 0.50 0.00 0.00) Converging n vectors ... it = 1 dn = 0.117E+01 rlx = 1.000 ( 66 ) it = 2 dn = 0.327E-15 rlx = 1.000 ( 81 ) Converging e1,e2 vectors ... it = 1 de = 0.357E+00 rlx = 1.000 ( 94 ) it = 2 de = 0.167E+00 rlx = 1.000 ( 67 ) it = 3 de = 0.245E-01 rlx = 1.000 ( 76 ) it = 4 de = 0.567E-02 rlx = 1.000 ( 59 ) it = 5 de = 0.192E-02 rlx = 1.000 ( 59 ) it = 6 de = 0.648E-03 rlx = 1.000 ( 59 ) it = 7 de = 0.219E-03 rlx = 1.000 ( 59 ) it = 8 de = 0.740E-04 rlx = 1.000 ( 59 ) it = 9 de = 0.250E-04 rlx = 1.000 ( 59 ) it = 10 de = 0.845E-05 rlx = 1.000 ( 59 ) it = 11 de = 0.286E-05 rlx = 1.000 ( 59 ) it = 12 de = 0.965E-06 rlx = 1.000 ( 59 ) it = 13 de = 0.326E-06 rlx = 1.000 ( 59 ) it = 14 de = 0.110E-06 rlx = 1.000 ( 59 ) it = 15 de = 0.372E-07 rlx = 1.000 ( 59 ) it = 16 de = 0.126E-07 rlx = 1.000 ( 59 ) it = 17 de = 0.425E-08 rlx = 1.000 ( 59 ) it = 18 de = 0.144E-08 rlx = 1.000 ( 59 ) it = 19 de = 0.485E-09 rlx = 1.000 ( 59 ) it = 20 de = 0.164E-09 rlx = 1.000 ( 59 ) Calculating strains, stress resultants ... Writing HSM solution to Tecplot File - hsm_CAPS.dat real 0m0.911s user 0m0.772s sys 0m0.077s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./hsmSimplePlateTest passed (as expected) ============================================= ================================================= + echo './hsmJoinedPlateTest test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt ./hsmJoinedPlateTest test; + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/cCAPSlog.txt + ./hsmJoinedPlateTest 0 Attention: hsmJoinedPlate is hard coded to look for ../csmData/feaJoinedPlate.csm Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plateTip, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Creating HSM BEM Getting quads for BEM! Number of nodal coordinates = 40 Number of elements = 56 Elemental Tria3 = 0 Elemental Quad4 = 16 Getting FEA materials....... Number of materials - 1 Material name - Madeupium No "materialType" specified for Material tuple Madeupium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate No "material" specified for Property tuple plate, defaulting to an index of 1 Done getting FEA properties Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA loads....... Number of loads - 1 Load name - appliedLoad Done getting FEA loads Writing Nastran grid and connectivity file (in small field format) .... Finished writing Nastran grid file Max Adjacency set to = 16 MaxDim = 13, numBCEdge = 2, numBCNode = 4, numJoint = 13 NEED TO ADD MORE CODE TO hsm_setGlobalParameter NEED TO ADD MORE CODE TO hsm_setNodeBCParameter NumBCNode = 4 ->HSMSOL Matrix Non-zero Entries = 1242 Converging HSM equation system ... iter dr dd dp rlx max 1 0.314E+01 0.628E+01 0.000E+00 0.080 ddx @ ( 1.00 0.00 0.00) 1* 0.341E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 1* 0.325E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.05 0.00) 1* 0.434E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 2 0.274E+01 0.521E+01 0.118E-07 0.096 ddx @ ( 1.00 0.05 0.00) 2* 0.321E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 2* 0.373E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.05 0.00) 2* 0.772E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.05 0.00) 3 0.202E+01 0.439E+01 0.107E-06 0.114 ddz @ ( 1.00 0.05 0.00) 3* 0.442E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.05 0.00) 3* 0.622E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.05 0.00) 3* 0.162E-03 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.05 0.00) 3* 0.163E-06 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 4 0.192E+01 0.476E+01 0.147E-07 0.105 ddz @ ( 1.00 0.05 0.00) 4* 0.335E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 4* 0.332E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 4* 0.448E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 5 0.187E+01 0.395E+01 0.296E-07 0.127 ddz @ ( 1.00 0.05 0.00) 5* 0.353E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 5* 0.379E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 5* 0.636E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 6 0.156E+01 0.301E+01 0.131E-06 0.166 ddx @ ( 1.00 0.05 0.00) 6* 0.326E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 6* 0.575E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 6* 0.191E-03 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 6* 0.265E-06 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 7 0.103E+01 0.323E+01 0.408E-07 0.155 ddx @ ( 1.00 0.05 0.00) 7* 0.259E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 7* 0.297E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 7* 0.432E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 8 0.757E+00 0.260E+01 0.162E-07 0.192 ddx @ ( 1.00 0.05 0.00) 8* 0.296E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 8* 0.351E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 8* 0.586E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 9 0.680E+00 0.181E+01 0.753E-07 0.276 ddx @ ( 0.88 0.00 0.00) 9* 0.329E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 9* 0.452E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 9* 0.159E-03 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 9* 0.238E-06 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 10 0.457E+00 0.172E+01 0.586E-07 0.290 ddz @ ( 1.00 0.10 0.00) 10* 0.166E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 10* 0.239E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 10* 0.392E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) iter dr dd dp rlx max 11 0.258E+00 0.122E+01 0.666E-08 0.411 ddz @ ( 1.00 0.10 0.00) 11* 0.207E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 11* 0.284E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 11* 0.486E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 12 0.135E+00 0.660E+00 0.377E-08 0.758 ddz @ ( 0.88 0.00 0.00) 12* 0.242E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 12* 0.368E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 12* 0.869E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 13 0.430E-01 0.257E+00 0.505E-07 1.000 ddx @ ( 1.00 0.05 0.00) 13* 0.395E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 13* 0.128E-03 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 13* 0.196E-06 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 14 0.656E-03 0.680E-02 0.885E-07 1.000 ddx @ ( 1.00 0.00 0.00) 15 0.156E-05 0.177E-05 0.268E-10 1.000 ddx @ ( 1.00 0.10 0.00) 16 0.273E-09 0.106E-08 0.893E-11 1.000 ddx @ ( 0.50 0.05 0.00) 17 0.138E-15 0.353E-15 0.907E-15 1.000 dps @ ( 0.38 0.10 0.00) Converging n vectors ... it = 1 dn = 0.197E+01 rlx = 1.000 ( 17 ) it = 2 dn = 0.866E-15 rlx = 1.000 ( 18 ) Converging e1,e2 vectors ... it = 1 de = 0.753E+01 rlx = 0.133 ( 1 ) it = 2 de = 0.309E+01 rlx = 0.324 ( 20 ) it = 3 de = 0.324E+01 rlx = 0.309 ( 2 ) it = 4 de = 0.226E+01 rlx = 0.443 ( 2 ) it = 5 de = 0.140E+01 rlx = 0.716 ( 4 ) it = 6 de = 0.660E+00 rlx = 1.000 ( 2 ) it = 7 de = 0.860E-01 rlx = 1.000 ( 4 ) it = 8 de = 0.228E-03 rlx = 1.000 ( 2 ) it = 9 de = 0.428E-11 rlx = 1.000 ( 4 ) Calculating strains, stress resultants ... Writing HSM solution to Tecplot File - hsm_CAPS.dat real 0m0.418s user 0m0.286s sys 0m0.077s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./hsmJoinedPlateTest passed (as expected) ============================================= Running.... AEROELASTIC c-Tests ================================================= Did not run examples for: awave pointwise Mystran ================================================= All tests pass! ================================================= ================================================= + ./execute_PyTestRegression.sh ================================================= Using python : /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/python ================================================= No options provided...defaulting to ALL Running.... LINEARAERO PyTests avl: /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/avl ================================================= + echo 'avl_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt avl_PyTest.py test; + python -u avl_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Loading AIM Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Writing surface - Wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) CXtot 0.0006119078685748102 CYtot -6.295467348382128e-15 CZtot -0.3012861394885953 Cltot -4.784258926526785e-14 Cmtot -0.1945055953450382 Cntot -2.338191252215186e-15 Cl'tot -4.787610967125373e-14 Cn'tot -1.502866821492718e-15 CLtot 0.3012509314150635 CDtot 0.004646353488232475 CDvis 0.0 CLff 0.3009503023520388 CYff -7.723329422293541e-15 CDind 0.004646353488232475 CDff 0.004968969500907922 e 0.9669902146157789 StripForces Wing cl = [0.02994790451347, 0.08555545178933, 0.1329003532587, 0.1733025192695, 0.2100182422833, 0.2453427152547, 0.2792746996365, 0.3101221284189, 0.3355632628223, 0.3531618776075, 0.3603457261533, 0.3542128805664, 0.3542128805661, 0.3603457261533, 0.3531618776088, 0.3355632628252, 0.3101221284236, 0.2792746996427, 0.2453427152623, 0.2100182422921, 0.17330251928, 0.1329003532723, 0.08555545180787, 0.0299479045408] Wing cd = [-0.004234137763162, -0.004494543653192, -0.003752887372724, -0.002739626801633, -0.001762021024326, -0.0007386538946409, 0.000511459807839, 0.0021191472861, 0.004145189908974, 0.006609094404181, 0.009540018987595, 0.01315518814708, 0.01315518814718, 0.009540018987792, 0.006609094404439, 0.00414518990926, 0.002119147286384, 0.0005114598080993, -0.0007386538944077, -0.001762021024096, -0.002739626801367, -0.003752887372445, -0.004494543653162, -0.004234137764545] real 0m1.447s user 0m0.987s sys 0m0.569s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case avl_PyTest.py passed (as expected) ================================================= ================================================= + echo 'avl_AutoSpan_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt avl_AutoSpan_PyTest.py test; + python -u avl_AutoSpan_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Loading AIM Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wing3, index = 3 Getting vortex lattice surface data VLM surface name - Wing1 VLM surface name - Wing2 VLM surface name - Wing3 Done getting vortex lattice surface data Warning: Control WingHinge1 not found in controls tuple! Only defaults will be used. Warning: Control WingHinge1 not found in controls tuple! Only defaults will be used. Warning: Control WingHinge1 not found in controls tuple! Only defaults will be used. Warning: Control WingHinge1 not found in controls tuple! Only defaults will be used. Writing surface - Wing1 (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Wing2 (ID = 1) Section 1 of 7 (ID = 0) Section 2 of 7 (ID = 1) Section 3 of 7 (ID = 2) Section 4 of 7 (ID = 3) Section 5 of 7 (ID = 4) Section 6 of 7 (ID = 5) Section 7 of 7 (ID = 6) Writing surface - Wing3 (ID = 2) Section 1 of 7 (ID = 0) Section 2 of 7 (ID = 3) Control surface 1 of 1 Section 3 of 7 (ID = 4) Control surface 1 of 1 Section 4 of 7 (ID = 1) Section 5 of 7 (ID = 5) Control surface 1 of 1 Section 6 of 7 (ID = 6) Control surface 1 of 1 Section 7 of 7 (ID = 2) CXtot -0.04120015370850767 CYtot -2.245617010841538e-10 CZtot -1.125018809209926 Cltot -1.249787598356312e-09 Cmtot -1.954741267455616 Cntot 1.914701795830442e-10 Cl'tot -1.246255634256898e-09 Cn'tot 2.132528188740779e-10 CLtot 1.124128421568333 CDtot 0.06082816423346078 CDvis 0.0 CLff 1.123105443194628 CYff -2.724471052441854e-10 CDind 0.06082816423346078 CDff -0.2032091360675605 e -0.3293037505974324 real 0m15.417s user 0m15.516s sys 0m3.255s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case avl_AutoSpan_PyTest.py passed (as expected) ================================================= ================================================= + echo 'avl_DesignSweep_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt avl_DesignSweep_PyTest.py test; + python -u avl_DesignSweep_PyTest.py -outLevel=0 -noPlotData + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002572533601556616 Cl = 0.2009337808875886 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002586364230247675 Cl = 0.2015191856817219 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002609799718822078 Cl = 0.2025075296435699 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002643444008430607 Cl = 0.2039185811661163 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002688200921004275 Cl = 0.2057816377792995 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002745342060022128 Cl = 0.2081373840562387 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002816610334305089 Cl = 0.2110406736708028 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002904376657741203 Cl = 0.2145646488018499 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003011879793049438 Cl = 0.2188068842337489 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003143602034593163 Cl = 0.2238987294818322 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003305877285459588 Cl = 0.2300199286489811 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003507917885480122 Cl = 0.237422386029936 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003763643677267996 Cl = 0.2464707142747725 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.004095167898235787 Cl = 0.2577158067750623 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.004540047408144598 Cl = 0.2720394012166634 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.005168237926862041 Cl = 0.290970150746647 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.006128930715340515 Cl = 0.3174875485939014 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.00781835905128463 Cl = 0.3586078919922491 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.01186220444375424 Cl = 0.4382638635248127 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002572533601556616 Cl = 0.2009337808875886 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002586364230247675 Cl = 0.2015191856817219 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002609799718822078 Cl = 0.2025075296435699 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002643444008430607 Cl = 0.2039185811661163 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002688200921004275 Cl = 0.2057816377792995 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002745342060022128 Cl = 0.2081373840562387 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002816610334305089 Cl = 0.2110406736708028 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002904376657741203 Cl = 0.2145646488018499 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003011879793049438 Cl = 0.2188068842337489 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003143602034593163 Cl = 0.2238987294818322 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003305877285459588 Cl = 0.2300199286489811 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003507917885480122 Cl = 0.237422386029936 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003763643677267996 Cl = 0.2464707142747725 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.004095167898235787 Cl = 0.2577158067750623 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.004540047408144598 Cl = 0.2720394012166634 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.005168237926862041 Cl = 0.290970150746647 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.006128930715340515 Cl = 0.3174875485939014 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.00781835905128463 Cl = 0.3586078919922491 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.01186220444375424 Cl = 0.4382638635248127 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002572533601556616 Cl = 0.2009337808875886 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002586364230247675 Cl = 0.2015191856817219 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002609799718822078 Cl = 0.2025075296435699 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002643444008430607 Cl = 0.2039185811661163 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002688200921004275 Cl = 0.2057816377792995 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002745342060022128 Cl = 0.2081373840562387 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002816610334305089 Cl = 0.2110406736708028 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.002904376657741203 Cl = 0.2145646488018499 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003011879793049438 Cl = 0.2188068842337489 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003143602034593163 Cl = 0.2238987294818322 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003305877285459588 Cl = 0.2300199286489811 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003507917885480122 Cl = 0.237422386029936 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.003763643677267996 Cl = 0.2464707142747725 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.004095167898235787 Cl = 0.2577158067750623 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.004540047408144598 Cl = 0.2720394012166634 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.005168237926862041 Cl = 0.290970150746647 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.006128930715340515 Cl = 0.3174875485939014 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.00781835905128463 Cl = 0.3586078919922491 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control Tail not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingRightLE not found in controls tuple! Only defaults will be used. Warning: Control WingRightTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Cd = 0.01186220444375424 Cl = 0.4382638635248127 Cl[0] = 0.2009337808875886 Cd[0] = 0.002572533601556616 real 0m54.736s user 0m23.284s sys 0m27.698s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case avl_DesignSweep_PyTest.py passed (as expected) ================================================= ================================================= + echo 'avl_ControlSurf_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt avl_ControlSurf_PyTest.py test; + python -u avl_ControlSurf_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Loading AIM Setting design parameters Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Vertical_Tail, index = 2 Getting vortex lattice control surface data VLM control surface name - Tail VLM control surface name - WingRightLE VLM control surface name - WingRightTE Done getting vortex lattice control surface data Getting vortex lattice surface data VLM surface name - Vertical_Tail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing Done getting vortex lattice surface data Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftLE not found in controls tuple! Only defaults will be used. Warning: Control WingLeftTE not found in controls tuple! Only defaults will be used. Writing surface - Vertical_Tail (ID = 0) Section 1 of 2 (ID = 0) Control surface 1 of 1 Section 2 of 2 (ID = 1) Control surface 1 of 1 Writing surface - Wing (ID = 1) Section 1 of 3 (ID = 1) Control surface 1 of 2 Control surface 2 of 2 Section 2 of 3 (ID = 0) Control surface 1 of 4 Control surface 2 of 4 Control surface 3 of 4 Control surface 4 of 4 Section 3 of 3 (ID = 2) Control surface 1 of 2 Control surface 2 of 2 Alpha 1.0 Beta 0.0 Mach 0.5 pb/2V -0.0 qc/2V 0.0 rb/2V -0.0 p'b/2V -0.0 r'b/2V -0.0 CXtot -0.01911479917643664 CYtot 0.03828770401119252 CZtot -0.6203123021542157 Cltot 0.0580302054292887 Cmtot -0.3649415791577237 Cntot -0.02051317548235195 Cl'tot 0.05766336287208888 Cn'tot -0.0215228179571592 CLtot 0.6198842263418534 CDtot 0.02993783031517985 CDvis 0.0 CLff 0.6192452092597066 CYff 0.0328707962584744 CDind 0.02993783031517985 CDff 0.02861019822661097 e 0.7130586920544685 real 0m1.809s user 0m1.212s sys 0m0.701s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case avl_ControlSurf_PyTest.py passed (as expected) ================================================= ================================================= + echo 'avl_EigenValue_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt avl_EigenValue_PyTest.py test; + python -u avl_EigenValue_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Loading AIM Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Writing surface - Wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing mass properties file: caps.mass Parsing MassProp Note: The following floating-point exceptions are signalling: IEEE_DIVIDE_BY_ZERO EigenValues {'case 1': [[0.48252996, 1.0092579], [0.48252996, -1.0092579], [-6.42569, 0.0], [-1.2733929, 0.0], [-0.0011487329, 0.0], [-1.2380479, 0.49321593], [-1.2380479, -0.49321593], [0.77888703, 0.0]]} real 0m1.490s user 0m0.963s sys 0m0.577s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case avl_EigenValue_PyTest.py passed (as expected) ================================================= ================================================= + echo 'avl_OpenMDAO_3_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt avl_OpenMDAO_3_PyTest.py test; + python -u avl_OpenMDAO_3_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt [macys-VM:40749] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/387973120/sm_segment.macys-VM.502.17200000.0 could be created. Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Getting vortex lattice surface data VLM surface name - Wing Done getting vortex lattice surface data Writing surface - Wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Alpha [2.] Beta [3.] Cmtot2 [0.04166298] Alpha [2.] Beta [3.] Cmtot2 [0.04166298] Cmtot2_Alpha [[0.68007176]] Cmtot2_Beta [[0.0008466]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 2 M = 10 At X0 0 variables are exactly at the bounds At iterate 0 f= 4.16630D-02 |proj g|= 6.80072D-01 Alpha [1.31992824] Beta [2.9991534] Cmtot2 [0.03401795] Cmtot2_Alpha [[0.60837327]] Cmtot2_Beta [[0.0015253]] At iterate 1 f= 3.40180D-02 |proj g|= 6.08373D-01 Alpha [-4.45133036] Beta [2.92288326] Cmtot2 [0.00071304] Cmtot2_Alpha [[0.07860089]] Cmtot2_Beta [[0.00107544]] At iterate 2 f= 7.13044D-04 |proj g|= 7.86009D-02 Alpha [-5.30773219] Beta [2.90057802] Cmtot2 [2.43104345e-05] Cmtot2_Alpha [[0.01420175]] Cmtot2_Beta [[0.00021881]] At iterate 3 f= 2.43104D-05 |proj g|= 1.42017D-02 Alpha [-5.49659696] Beta [2.89526135] Cmtot2 [3.72334447e-08] Cmtot2_Alpha [[0.00055304]] Cmtot2_Beta [[8.7325759e-06]] At iterate 4 f= 3.72334D-08 |proj g|= 5.53036D-04 Alpha [-5.50424967] Beta [2.89504288] Cmtot2 [2.19764579e-12] Cmtot2_Alpha [[4.24793143e-06]] Cmtot2_Beta [[6.71418674e-08]] At iterate 5 f= 2.19765D-12 |proj g|= 4.24793D-06 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 2 5 6 5 0 0 4.248D-06 2.198D-12 F = 2.1976457892812188E-012 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- Optimized values: [-5.50424967] [2.89504288] real 0m32.999s user 0m8.112s sys 0m2.974s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case avl_OpenMDAO_3_PyTest.py passed (as expected) ================================================= friction: /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/friction ================================================= + echo 'friction_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt friction_PyTest.py test; + python -u friction_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Loading AIM Setting Mach & Altitude Values Lifting Surface: Body = 1, units m XLE: 1.571946 -3.872983 0.249728 XTE: 2.536563 -3.872983 0.335335 Chord: 0.968408 Arc: 1.985181 T/C: 0.155975 Type: Wing Lifting Surface: Body = 2, units m XLE: 0.000000 0.000000 0.000000 XTE: 1.614012 0.000000 0.002015 Chord: 1.614013 Arc: 3.308635 T/C: 0.127839 Type: Wing Lifting Surface: Body = 3, units m XLE: 1.571946 3.872983 0.249728 XTE: 2.536563 3.872983 0.335335 Chord: 0.968408 Arc: 1.985181 T/C: 0.155975 Type: Wing Lifting Surface: Body = 4, units m XLE: 5.484123 0.000000 1.468246 XTE: 6.210307 0.000915 1.468246 Chord: 0.726185 Arc: 1.482717 T/C: 0.120035 Type: VTail Lifting Surface: Body = 5, units m XLE: 5.000000 0.000000 0.500000 XTE: 6.210307 0.001525 0.500000 Chord: 1.210308 Arc: 2.471195 T/C: 0.120035 Type: VTail Lifting Surface: Body = 6, units m XLE: 5.484123 -0.968246 0.500000 XTE: 6.210307 -0.968246 0.500915 Chord: 0.726185 Arc: 1.482717 T/C: 0.120035 Type: HTail Lifting Surface: Body = 7, units m XLE: 5.484123 0.968246 0.500000 XTE: 6.210307 0.968246 0.500915 Chord: 0.726185 Arc: 1.482717 T/C: 0.120035 Type: HTail Body of Revolution: Body = 8, units m Arc: 0.000000 Diameter: 0.000000 Type: Fuse Body of Revolution: Body = 9, units m Arc: 3.714180 Diameter: 1.020621 Type: Fuse Body of Revolution: Body = 10, units m Arc: 2.771209 Diameter: 0.645497 Type: Fuse Body of Revolution: Body = 11, units m Arc: 1.013945 Diameter: 0.322749 Type: Fuse Body of Revolution: Body = 12, units m Arc: 0.101394 Diameter: 0.032275 Type: Fuse Number of sections 4, number of revolution sections 1 Number of Mach-Altitude cases = 2 Total drag = [0.0132, 0.01226] Form drag = [0.0033, 0.00307] Friction drag = [0.0099, 0.00919] real 0m1.144s user 0m0.956s sys 0m0.312s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case friction_PyTest.py passed (as expected) ================================================= tsfoil2: /Users/jenkins/util/tsfoil/tsfoil2 ================================================= + echo 'tsfoil_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt tsfoil_PyTest.py test; + python -u tsfoil_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Getting results PAUSE Press the ENTER key to exit To resume execution, type go. Other input will terminate the job. Cl = 0.933417 Cd = 0.000284 Cd Wave = 0.0 Cm = -0.203436 Cp _Critcal = -1.303869 real 0m1.196s user 0m0.954s sys 0m0.278s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case tsfoil_PyTest.py passed (as expected) ================================================= mses: /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/mses ================================================= + echo 'mses_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt mses_PyTest.py test; + python -u mses_PyTest.py -outLevel=0 -noPlotData + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Cl = 0.37837932402995744 Cd = 0.0077758580442312715 Cm = 0.005262576090327783 real 0m4.329s user 0m3.899s sys 0m0.462s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case mses_PyTest.py passed (as expected) ================================================= ================================================= + echo 'mses_OpenMDAO_3_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt mses_OpenMDAO_3_PyTest.py test; + python -u mses_OpenMDAO_3_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt [macys-VM:40878] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/3571384320/sm_segment.macys-VM.502.d4df0000.0 could be created. Getting CFD design variables....... Number of design variables - 1 Design Variable name - camber Done getting CFD design variables camber [0.1] CD [0.01326534] camber [0.1] CD [0.01326534] CD_camber [[0.17647556]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 1 M = 10 At X0 1 variables are exactly at the bounds At iterate 0 f= 1.32653D-02 |proj g|= 1.76476D-01 camber [-0.07647556] CD [0.01022329] CD_camber [[-0.08760106]] At iterate 1 f= 1.02233D-02 |proj g|= 8.76011D-02 camber [-0.01793405] CD [0.00770371] CD_camber [[-0.01328824]] At iterate 2 f= 7.70371D-03 |proj g|= 1.32882D-02 camber [-0.00746595] CD [0.00760241] CD_camber [[-0.00542349]] At iterate 3 f= 7.60241D-03 |proj g|= 5.42349D-03 camber [-0.00024721] CD [0.00758207] CD_camber [[-0.00011833]] At iterate 4 f= 7.58207D-03 |proj g|= 1.18327D-04 camber [-8.62005111e-05] CD [0.00758208] CD_camber [[-3.2293282e-06]] camber [-0.00022068] CD [0.00758207] CD_camber [[-0.00010202]] At iterate 5 f= 7.58207D-03 |proj g|= 1.02022D-04 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 1 5 7 5 0 0 1.020D-04 7.582D-03 F = 7.5820696804286096E-003 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- Optimized values: [-0.00022068] real 0m29.013s user 0m27.369s sys 0m1.741s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case mses_OpenMDAO_3_PyTest.py passed (as expected) ================================================= xfoil: /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/xfoil ================================================= + echo 'xfoil_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt xfoil_PyTest.py test; + python -u xfoil_PyTest.py -outLevel=0 -noPlotData + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Cl = [1.05475230553347, 1.36488869373699, 1.5660721427216, 2.03059709348412, 1.97271083121139, 1.87307153172667, 1.7605047576018] Cd = [0.0131991208677172, 0.0166540240605863, 0.0200551482562954, 0.0458671341943513, 0.07542560093961, 0.099446917447585, 0.127479430989108] Alpha = [0.0, 3.0, 5.0, 11.0, 13.0, 14.0, 15.0] Transition location = [0.496044115314418, 0.46137773204142, 0.442376568201556, 0.361251636297643, 0.276104140853528, 0.214381239319783, 0.132988264746104] real 0m5.379s user 0m5.129s sys 0m0.339s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case xfoil_PyTest.py passed (as expected) ================================================= Running.... MESH PyTests ================================================= + echo 'egadsTess_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt egadsTess_PyTest.py test; + python -u egadsTess_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = Ribs, index = 1 Name = Skin, index = 2 Name = Spar1, index = 3 Name = Rib_Root, index = 4 Name = Spar2, index = 5 Name = Rib_Root_Point, index = 6 Name = Wing, index = 7 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = LeadingEdge, index = 1 Name = TrailingEdge, index = 2 Getting mesh sizing parameters Mesh sizing name - LeadingEdge Done getting mesh sizing parameters Getting surface mesh for body 1 (of 4) Getting surface mesh for body 2 (of 4) Getting surface mesh for body 3 (of 4) Getting surface mesh for body 4 (of 4) Body 1 (of 4) Number of nodes = 3793 Number of elements = 4001 Number of triangle elements = 0 Number of quadrilateral elements = 4001 Body 2 (of 4) Number of nodes = 1 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 Body 3 (of 4) Number of nodes = 76 Number of elements = 55 Number of triangle elements = 0 Number of quadrilateral elements = 55 Body 4 (of 4) Number of nodes = 100 Number of elements = 73 Number of triangle elements = 0 Number of quadrilateral elements = 73 ---------------------------- Total number of nodes = 3970 Total number of elements = 4129 Writing Tecplot file .... Finished writing Tecplot file Writing ASCII STL file .... Finished writing ASCII STL file Writing ugrid file .... Finished writing ugrid file real 0m9.176s user 0m15.854s sys 0m1.882s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case egadsTess_PyTest.py passed (as expected) ================================================= ================================================= + echo 'egadsTess_Box_Quad_Pytest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt egadsTess_Box_Quad_Pytest.py test; + python -u egadsTess_Box_Quad_Pytest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = box1, index = 1 Name = box2, index = 2 Name = box3, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Face 3 TFI quading disabled with attribute .qParams Face 4 TFI quading disabled with attribute .qParams TFI quading on all faces disabled with .qParams attribute on the body Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 602 Number of elements = 600 Number of triangle elements = 0 Number of quadrilateral elements = 600 Body 2 (of 3) Number of nodes = 537 Number of elements = 535 Number of triangle elements = 0 Number of quadrilateral elements = 535 Body 3 (of 3) Number of nodes = 1356 Number of elements = 1354 Number of triangle elements = 0 Number of quadrilateral elements = 1354 ---------------------------- Total number of nodes = 2495 Total number of elements = 2489 Writing Tecplot file .... Finished writing Tecplot file Writing ASCII STL file .... Finished writing ASCII STL file Writing ugrid file .... Finished writing ugrid file real 0m5.235s user 0m5.868s sys 0m0.223s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case egadsTess_Box_Quad_Pytest.py passed (as expected) ================================================= ================================================= + echo 'egadsTess_Spheres_Quad_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt egadsTess_Spheres_Quad_PyTest.py test; + python -u egadsTess_Spheres_Quad_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Spheres, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Face 4 has a degenerate edge - no TFI quading Face 5 has a degenerate edge - no TFI quading Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 6276 Number of elements = 6274 Number of triangle elements = 0 Number of quadrilateral elements = 6274 ---------------------------- Total number of nodes = 6276 Total number of elements = 6274 Writing Tecplot file .... Finished writing Tecplot file Writing ASCII STL file .... Finished writing ASCII STL file Writing ugrid file .... Finished writing ugrid file real 0m8.145s user 0m11.184s sys 0m0.318s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case egadsTess_Spheres_Quad_PyTest.py passed (as expected) ================================================= ================================================= + echo 'egadsTess_Nose_Quad_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt egadsTess_Nose_Quad_PyTest.py test; + python -u egadsTess_Nose_Quad_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = nose, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Face 2 has a degenerate edge - no TFI quading Getting surface mesh for body 1 (of 1) EG_getSidepoint: LineSearch Failed (0.000000 0.973785)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (1.013231 0.966690)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (1.004202 0.966536)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (1.004202 0.966536)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (1.004202 0.966536)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (1.004202 0.966536)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (1.046938 0.962477)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (1.035914 0.957483)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (1.015407 0.966058)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (0.856444 0.971910)! EG_getSidepoint: LineSearch Failed (2.750998 0.986828)! EG_getSidepoint: LineSearch Failed (0.813517 0.972994)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! EG_getSidepoint: LineSearch Failed (0.719835 0.974156)! Body 1 (of 1) Number of nodes = 1480 Number of elements = 1478 Number of triangle elements = 0 Number of quadrilateral elements = 1478 ---------------------------- Total number of nodes = 1480 Total number of elements = 1478 Writing Tecplot file .... Finished writing Tecplot file Writing ASCII STL file .... Finished writing ASCII STL file Writing ugrid file .... Finished writing ugrid file real 0m4.424s user 0m4.738s sys 0m0.317s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case egadsTess_Nose_Quad_PyTest.py passed (as expected) ================================================= ================================================= + echo 'aflr2_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr2_PyTest.py test; + python -u aflr2_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 344 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 344 344 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 70 142 AFLR2 IG : Nodes, Faces = 140 282 AFLR2 IG : Nodes, Faces = 210 422 AFLR2 IG : Nodes, Faces = 280 562 AFLR2 IG : Nodes, Faces = 316 634 AFLR2 IG : Nodes, Faces = 344 690 AFLR2 IG : Nodes, Faces = 348 690 AFLR2 IG : Nodes, Faces = 344 344 AFLR2 : CPU Time = 0.001 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GGp: Nodes, Faces = 344 344 AFLR2 GGp: Nodes, Faces = 681 1018 AFLR2 GGp: Nodes, Faces = 1013 1682 AFLR2 GGp: Nodes, Faces = 1339 2334 AFLR2 GGp: Nodes, Faces = 1652 2960 AFLR2 GGp: Nodes, Faces = 1957 3570 AFLR2 GGp: Nodes, Faces = 2252 4160 AFLR2 GGp: Nodes, Faces = 2526 4708 AFLR2 GGp: Nodes, Faces = 2809 5274 AFLR2 GGp: Nodes, Faces = 3083 5822 AFLR2 GGp: Nodes, Faces = 3327 6310 AFLR2 GGp: Nodes, Faces = 3564 6784 AFLR2 GGp: Nodes, Faces = 3788 7232 AFLR2 GGp: Nodes, Faces = 3995 7646 AFLR2 GGp: Nodes, Faces = 4194 8044 AFLR2 GGp: Nodes, Faces = 4394 8444 AFLR2 GGp: Nodes, Faces = 4585 8826 AFLR2 GGp: Nodes, Faces = 4772 9200 AFLR2 GGp: Nodes, Faces = 4943 9542 AFLR2 GGp: Nodes, Faces = 5129 9914 AFLR2 GGp: Nodes, Faces = 5293 10242 AFLR2 GGp: Nodes, Faces = 5447 10550 AFLR2 GGp: Nodes, Faces = 5594 10844 AFLR2 GGp: Nodes, Faces = 5716 11088 AFLR2 GGp: Nodes, Faces = 5830 11316 AFLR2 GGp: Nodes, Faces = 5909 11474 AFLR2 GGp: Nodes, Faces = 5964 11584 AFLR2 GGp: Nodes, Faces = 6006 11668 AFLR2 GGp: Nodes, Faces = 6025 11706 AFLR2 GGp: Nodes, Faces = 6034 11724 AFLR2 : CPU Time = 0.021 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 6034 11724 AFLR2 QI : Nodes, Faces = 6033 454 AFLR2 QI : Nodes, Faces = 6033 5634 AFLR2 QI : Nodes, Faces = 6033 11722 AFLR2 QI : Nodes, Faces = 6032 462 AFLR2 QI : Nodes, Faces = 6032 5629 AFLR2 QI : Nodes, Faces = 6032 11720 AFLR2 QI : Nodes, Faces = 6032 456 AFLR2 QI : Nodes, Faces = 6032 5632 AFLR2 QI : Nodes, Faces = 6032 11720 AFLR2 QI : Nodes, Faces = 6032 474 AFLR2 QI : Nodes, Faces = 6032 5623 AFLR2 QI : Nodes, Faces = 6032 11720 AFLR2 QI : Nodes, Faces = 6031 486 AFLR2 QI : Nodes, Faces = 6031 5616 AFLR2 QI : Nodes, Faces = 6031 488 AFLR2 QI : Nodes, Faces = 6031 5616 AFLR2 : CPU Time = 0.011 seconds AFLR2 : DONE EGADS Internal: Face 1, Side 4741 4722 complete [but 7915] (EG_makeConnect)! EGADS Internal: Face 1, Side 4741 4912 complete [but 7916] (EG_makeConnect)! EGADS Internal: Face 1, Side 5850 5858 complete [but 8742] (EG_makeConnect)! EGADS Internal: Face 1, Side 5850 5851 complete [but 8742] (EG_makeConnect)! EGADS Internal: Face 1, Side 5858 5851 complete [but 8791] (EG_makeConnect)! EGADS Internal: Face 1, Side 4912 4722 complete [but 9417] (EG_makeConnect)! Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 6031 Number of elements = 6448 Number of tris = 488 Number of quad = 5616 EGADS Internal: Face 1, Side 4741 4722 complete [but 7915] (EG_makeConnect)! EGADS Internal: Face 1, Side 4741 4912 complete [but 7916] (EG_makeConnect)! EGADS Internal: Face 1, Side 5850 5858 complete [but 8742] (EG_makeConnect)! EGADS Internal: Face 1, Side 5850 5851 complete [but 8742] (EG_makeConnect)! EGADS Internal: Face 1, Side 5858 5851 complete [but 8791] (EG_makeConnect)! EGADS Internal: Face 1, Side 4912 4722 complete [but 9417] (EG_makeConnect)! EGADS Internal: Face 1, Side 4741 4722 complete [but 7915] (EG_makeConnect)! EGADS Internal: Face 1, Side 4741 4912 complete [but 7916] (EG_makeConnect)! EGADS Internal: Face 1, Side 5850 5858 complete [but 8742] (EG_makeConnect)! EGADS Internal: Face 1, Side 5850 5851 complete [but 8742] (EG_makeConnect)! EGADS Internal: Face 1, Side 5858 5851 complete [but 8791] (EG_makeConnect)! EGADS Internal: Face 1, Side 4912 4722 complete [but 9417] (EG_makeConnect)! Writing Tecplot file .... Tecplot expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing Tecplot file real 0m1.335s user 0m1.251s sys 0m0.390s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr2_PyTest.py passed (as expected) ================================================= ================================================= + echo 'aflr4_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr4_PyTest.py test; + python -u aflr4_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Writing ASCII STL file .... Finished writing ASCII STL file Writing ugrid file .... Finished writing ugrid file real 0m3.270s user 0m2.826s sys 0m0.504s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr4_PyTest.py passed (as expected) ================================================= ================================================= + echo 'aflr4_Symmetry_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr4_Symmetry_PyTest.py test; + python -u aflr4_Symmetry_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Farfield, index = 1 Name = Symmetry, index = 2 Name = Wing1, index = 3 Name = Wing2, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = Symmetry, index = 2 Name = Wing1, index = 3 Name = Wing2, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - Symmetry Done getting mesh sizing parameters AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file real 0m3.375s user 0m3.058s sys 0m0.555s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr4_Symmetry_PyTest.py passed (as expected) ================================================= ================================================= + echo 'aflr4_Generic_Missile.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr4_Generic_Missile.py test; + python -u aflr4_Generic_Missile.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = MissileOML, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file real 0m8.219s user 0m10.618s sys 0m0.787s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr4_Generic_Missile.py passed (as expected) ================================================= ================================================= + echo 'aflr4_TipTreat_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr4_TipTreat_PyTest.py test; + python -u aflr4_TipTreat_PyTest.py -outLevel=0 -noPlotData + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Writing Tecplot file .... Finished writing Tecplot file real 0m10.002s user 0m9.267s sys 0m0.754s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr4_TipTreat_PyTest.py passed (as expected) ================================================= ================================================= + echo 'aflr4_and_aflr3_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr4_and_aflr3_PyTest.py test; + python -u aflr4_and_aflr3_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Writing ASCII STL file .... Finished writing ASCII STL file Writing ugrid file .... Finished writing ugrid file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Getting mesh sizing parameters Mesh sizing name - Wing1 Mesh sizing name - Wing2 Done getting mesh sizing parameters Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 150173 Number of elements = 449915 Number of triangles = 14380 Number of quadrilatarals = 0 Number of tetrahedrals = 214483 Number of pyramids = 425 Number of prisms = 220627 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file real 0m18.986s user 0m17.788s sys 0m1.008s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr4_and_aflr3_PyTest.py passed (as expected) ================================================= ================================================= + echo 'aflr4_and_aflr3_Symmetry_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr4_and_aflr3_Symmetry_PyTest.py test; + python -u aflr4_and_aflr3_Symmetry_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Farfield, index = 1 Name = Symmetry, index = 2 Name = Wing1, index = 3 Name = Wing2, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = Symmetry, index = 2 Name = Wing1, index = 3 Name = Wing2, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - Symmetry Done getting mesh sizing parameters AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Farfield, index = 1 Name = Symmetry, index = 2 Name = Wing1, index = 3 Name = Wing2, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Farfield, index = 1 Name = Symmetry, index = 2 Name = Wing1, index = 3 Name = Wing2, index = 4 Getting mesh sizing parameters Mesh sizing name - Wing1 Mesh sizing name - Wing2 Done getting mesh sizing parameters Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 332982 Number of elements = 1068590 Number of triangles = 44340 Number of quadrilatarals = 1613 Number of tetrahedrals = 573242 Number of pyramids = 327 Number of prisms = 449068 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file real 0m36.572s user 0m34.162s sys 0m1.651s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr4_and_aflr3_Symmetry_PyTest.py passed (as expected) ================================================= ================================================= + echo 'aflr4_QuadMesh_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr4_QuadMesh_PyTest.py test; + python -u aflr4_QuadMesh_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = Ribs, index = 1 Name = Skin, index = 2 Name = Spar1, index = 3 Name = Rib_Root, index = 4 Name = Spar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = LeadingEdge, index = 1 Name = TrailingEdge, index = 2 Writing Tecplot file .... Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file real 0m9.913s user 0m16.535s sys 0m1.772s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr4_QuadMesh_PyTest.py passed (as expected) ================================================= ================================================= + echo 'aflr4_and_Tetgen_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr4_and_Tetgen_PyTest.py test; + python -u aflr4_and_Tetgen_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 30045, elements - 60078 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Writing Tecplot file .... Finished writing Tecplot file real 0m15.953s user 0m14.626s sys 0m1.086s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr4_and_Tetgen_PyTest.py passed (as expected) ================================================= ================================================= + echo 'aflr4_tetgen_Regions_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aflr4_tetgen_Regions_PyTest.py test; + python -u aflr4_tetgen_Regions_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = cut, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 1 Active Bodies EGADS : Body 0 is a SheetBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 11 Faces EGADS : Body 0 has 20 Edges EGADS : Body 0 has 11 Loops EGADS : Body 0 has 12 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 6 8 10 11 EGADS : 2 Yes 0 0 1 0 1 1 3 7 9 11 EGADS : 3 Yes 0 0 1 0 1 2 4 6 9 11 EGADS : 4 Yes 0 0 1 0 1 3 5 7 9 11 EGADS : 5 Yes 0 0 1 0 1 4 6 8 10 11 EGADS : 6 Yes 0 0 1 0 1 1 3 5 10 11 EGADS : 7 Yes 0 0 1 0 1 2 4 8 9 11 EGADS : 8 Yes 0 0 1 0 1 1 5 7 10 11 EGADS : 9 Yes 0 0 1 0 1 2 3 4 7 EGADS : 10 Yes 0 0 1 0 1 1 5 6 8 EGADS : 11 Yes 0 0 1 0 1 1 2 3 4 5 6 7 8 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 6 7 -2 EGADS : 3 8 5 9 -10 EGADS : 4 10 11 -12 -13 EGADS : 5 14 15 -16 -11 EGADS : 6 1 -17 -14 -9 EGADS : 7 -18 12 -19 -7 EGADS : 8 16 20 -3 19 EGADS : 9 13 18 -6 -8 EGADS : 10 -15 17 4 -20 EGADS : 11 11 -19 -2 9 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 6 7 -2 EGADS : 3 Yes 8 5 9 -10 EGADS : 4 Yes 10 11 -12 -13 EGADS : 5 Yes 14 15 -16 -11 EGADS : 6 Yes 1 -17 -14 -9 EGADS : 7 Yes -18 12 -19 -7 EGADS : 8 Yes 16 20 -3 19 EGADS : 9 Yes 13 18 -6 -8 EGADS : 10 Yes -15 17 4 -20 EGADS : 11 Yes 11 -19 -2 9 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 6 EGADS : 2 0 Yes 1 3 1 1 2 11 EGADS : 3 0 Yes 3 4 1 1 8 EGADS : 4 0 Yes 2 4 1 1 10 EGADS : 5 0 Yes 5 1 1 2 3 EGADS : 6 0 Yes 5 6 1 2 9 EGADS : 7 0 Yes 6 3 1 2 7 EGADS : 8 0 Yes 7 5 1 3 9 EGADS : 9 0 Yes 1 8 1 3 6 11 EGADS : 10 0 Yes 7 8 1 3 4 EGADS : 11 0 Yes 8 9 1 4 5 11 EGADS : 12 0 Yes 10 9 1 4 7 EGADS : 13 0 Yes 7 10 1 4 9 EGADS : 14 0 Yes 8 11 1 5 6 EGADS : 15 0 Yes 11 12 1 5 10 EGADS : 16 0 Yes 9 12 1 5 8 EGADS : 17 0 Yes 11 2 1 6 10 EGADS : 18 0 Yes 10 6 1 7 9 EGADS : 19 0 Yes 3 9 1 7 8 11 EGADS : 20 0 Yes 12 4 1 8 10 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 1 0 0 EGADS : 2 Yes 1 0 2 EGADS : 3 Yes 1 1 1 EGADS : 4 Yes 1 1 2 EGADS : 5 Yes 1 0 0 EGADS : 6 Yes 1 1 0 EGADS : 7 Yes 0 0 0 EGADS : 8 Yes 0 0 0 EGADS : 9 Yes 0 1 1 EGADS : 10 Yes 0 1 0 EGADS : 11 Yes 0 0 2 EGADS : 12 Yes 0 1 2 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 4 AFLR4 : Min Bounding Box Length = 2 AFLR4 : Max Ref Bounding Box Length = 4 AFLR4 : Min Ref Bounding Box Length = 2 AFLR4 : Reference Length = 1 AFLR4 : BL Thickness = 0 AFLR4 : Abs Min Surf Spacing = 0.0025 AFLR4 : Min Surf Spacing = 0.01 AFLR4 : Max Surf Spacing = 0.2 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 TRANSP AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 137 228 0 AFLR4 : Nodes, Trias,Quads= 131 216 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 137 228 0 AFLR4 : Nodes, Trias,Quads= 132 218 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 76 120 0 AFLR4 : Nodes, Trias,Quads= 72 112 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 137 228 0 AFLR4 : Nodes, Trias,Quads= 132 218 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 137 228 0 AFLR4 : Nodes, Trias,Quads= 131 216 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 196 340 0 AFLR4 : Nodes, Trias,Quads= 192 332 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 196 340 0 AFLR4 : Nodes, Trias,Quads= 192 332 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 76 120 0 AFLR4 : Nodes, Trias,Quads= 72 112 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 134 226 0 AFLR4 : Nodes, Trias,Quads= 132 222 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 135 228 0 AFLR4 : Nodes, Trias,Quads= 131 220 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 184 318 0 AFLR4 : Nodes, Trias,Quads= 178 306 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 1231 2504 464 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 1231 2504 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 140 234 0 AFLR4 : Nodes, Trias,Quads= 134 222 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 140 234 0 AFLR4 : Nodes, Trias,Quads= 133 220 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 76 120 0 AFLR4 : Nodes, Trias,Quads= 72 112 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 140 234 0 AFLR4 : Nodes, Trias,Quads= 133 220 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 141 236 0 AFLR4 : Nodes, Trias,Quads= 133 220 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 207 362 0 AFLR4 : Nodes, Trias,Quads= 193 334 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 203 354 0 AFLR4 : Nodes, Trias,Quads= 193 334 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 76 120 0 AFLR4 : Nodes, Trias,Quads= 72 112 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 136 230 0 AFLR4 : Nodes, Trias,Quads= 132 222 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 137 232 0 AFLR4 : Nodes, Trias,Quads= 132 222 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 193 336 0 AFLR4 : Nodes, Trias,Quads= 183 316 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 1246 2534 464 OVERALL : CPU Time = 0.115 seconds Body 1 (of 1) Number of nodes = 1246 Number of elements = 2534 Number of triangle elements = 2534 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 1246 Total number of elements = 2534 Total number of triangle elements = 2534 Total number of quadrilateral elements = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = cut, index = 2 Number of surface: nodes - 1246, elements - 2534 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.009396 Creating surface mesh ... Surface mesh seconds: 0.002742 Recovering boundaries... Boundary recovery seconds: 0.006752 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.000881 Recovering Delaunayness... Delaunay recovery seconds: 0.002417 Refining mesh... Refinement seconds: 0.014135 Smoothing vertices... Mesh smoothing seconds: 0.015614 Improving mesh... Mesh improvement seconds: 0.001269 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.000675 Total running seconds: 0.054111 Statistics: Input points: 1246 Input facets: 2534 Input segments: 3777 Input holes: 0 Input regions: 2 Mesh points: 1455 Mesh tetrahedra: 5105 Mesh faces: 11319 Mesh faces on exterior boundary: 2218 Mesh faces on input facets: 2534 Mesh edges on input segments: 3777 Steiner points inside domain: 209 Done meshing using TetGen! Writing vtk file .... Writing vtk general file .... Finished writing vtk file Writing Tecplot file .... Finished writing Tecplot file real 0m1.074s user 0m0.943s sys 0m0.267s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aflr4_tetgen_Regions_PyTest.py passed (as expected) ================================================= ================================================= + echo 'tetgen_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt tetgen_PyTest.py test; + python -u tetgen_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 2236 Number of elements = 4468 Number of triangle elements = 4468 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 636 Number of elements = 1268 Number of triangle elements = 1268 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 267 Number of elements = 530 Number of triangle elements = 530 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3139 Total number of elements = 6266 Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 3139, elements - 6266 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.027769 Creating surface mesh ... Surface mesh seconds: 0.007518 Recovering boundaries... Boundary recovery seconds: 0.09405 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.008772 Suppressing Steiner points ... Steiner suppression seconds: 4.8e-05 Recovering Delaunayness... Delaunay recovery seconds: 0.014866 Refining mesh... 4188 insertions, added 2137 points, 127272 tetrahedra in queue. 1394 insertions, added 414 points, 131442 tetrahedra in queue. 1858 insertions, added 464 points, 129858 tetrahedra in queue. 2477 insertions, added 450 points, 111812 tetrahedra in queue. 3302 insertions, added 490 points, 67833 tetrahedra in queue. 4401 insertions, added 401 points, 112 tetrahedra in queue. Refinement seconds: 0.932153 Smoothing vertices... Mesh smoothing seconds: 0.480195 Improving mesh... Mesh improvement seconds: 0.009557 Jettisoning redundant points. Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.00311 Total running seconds: 1.57858 Statistics: Input points: 3139 Input facets: 6266 Input segments: 9399 Input holes: 2 Input regions: 0 Mesh points: 7895 Mesh tetrahedra: 38676 Mesh faces: 80485 Mesh faces on exterior boundary: 6266 Mesh faces on input facets: 6266 Mesh edges on input segments: 9399 Steiner points inside domain: 4756 Done meshing using TetGen! Writing Tecplot file .... Finished writing Tecplot file real 0m6.815s user 0m5.913s sys 0m0.445s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case tetgen_PyTest.py passed (as expected) ================================================= ================================================= + echo 'tetgen_Holes_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt tetgen_Holes_PyTest.py test; + python -u tetgen_Holes_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = cut, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 8995 Number of elements = 18112 Number of triangle elements = 18112 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 8995 Total number of elements = 18112 Writing Tecplot file .... Finished writing Tecplot file Writing vtk file .... Writing vtk surface file .... capsGroups found: 1: box 2: cut Finished writing vtk file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = cut, index = 2 Number of surface: nodes - 8995, elements - 18112 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.214476 Creating surface mesh ... Surface mesh seconds: 0.019752 Recovering boundaries... Boundary recovery seconds: 0.111954 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.018024 Recovering Delaunayness... Delaunay recovery seconds: 0.053802 Refining mesh... Refinement seconds: 0.268236 Smoothing vertices... Mesh smoothing seconds: 0.327353 Improving mesh... Mesh improvement seconds: 0.011403 Jettisoning redundant points. Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.005069 Total running seconds: 1.03115 Statistics: Input points: 8995 Input facets: 18112 Input segments: 27104 Input holes: 1 Input regions: 0 Mesh points: 7140 Mesh tetrahedra: 27881 Mesh faces: 60802 Mesh faces on exterior boundary: 10080 Mesh faces on input facets: 10080 Mesh edges on input segments: 15120 Steiner points inside domain: 2098 Done meshing using TetGen! Volume mesher did not preserve surface elements - data transfer will NOT be possible. Writing Tecplot file .... Finished writing Tecplot file Writing vtk file .... Writing vtk general file .... Finished writing vtk file real 0m2.648s user 0m2.427s sys 0m0.322s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case tetgen_Holes_PyTest.py passed (as expected) ================================================= ================================================= + echo 'tetgen_Regions_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt tetgen_Regions_PyTest.py test; + python -u tetgen_Regions_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = cut, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 8995 Number of elements = 18112 Number of triangle elements = 18112 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 8995 Total number of elements = 18112 Writing Tecplot file .... Finished writing Tecplot file Writing vtk file .... Writing vtk surface file .... capsGroups found: 1: box 2: cut Finished writing vtk file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = box, index = 1 Name = cut, index = 2 Number of surface: nodes - 8995, elements - 18112 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.202696 Creating surface mesh ... Surface mesh seconds: 0.020815 Recovering boundaries... Boundary recovery seconds: 0.101866 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.00932 Recovering Delaunayness... Delaunay recovery seconds: 0.094623 Refining mesh... Refinement seconds: 0.488791 Smoothing vertices... Mesh smoothing seconds: 0.609855 Improving mesh... Mesh improvement seconds: 0.016306 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.006347 Total running seconds: 1.5517 Statistics: Input points: 8995 Input facets: 18112 Input segments: 27104 Input holes: 0 Input regions: 2 Mesh points: 13181 Mesh tetrahedra: 55765 Mesh faces: 119562 Mesh faces on exterior boundary: 16064 Mesh faces on input facets: 18112 Mesh edges on input segments: 27104 Steiner points inside domain: 4186 Done meshing using TetGen! Writing Tecplot file .... Finished writing Tecplot file Writing vtk file .... Writing vtk general file .... Finished writing vtk file real 0m3.313s user 0m3.019s sys 0m0.340s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case tetgen_Regions_PyTest.py passed (as expected) ================================================= delaundo: /Users/jenkins/util/delaundo/delaundo/src/delaundo ================================================= + echo 'delaundo_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt delaundo_PyTest.py test; + python -u delaundo_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Name = AirfoilTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 6 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Name = AirfoilTE, index = 6 Getting mesh sizing parameters Mesh sizing name - Airfoil Mesh sizing name - AirfoilTE Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting edge discretization for body 1 Delaundo expects 2D meshes in the x-y plane... attempting to rotate mesh through node swapping! Swapping z and y coordinates! Writing delaundo control file - delaundo.ctr Writing out *.pts file Reading delaundo mesh file - delaundo_CAPS.mesh Swapping y and z coordinates! Writing Tecplot file .... Tecplot expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing Tecplot file Writing ugrid file .... Finished writing ugrid file real 0m1.380s user 0m1.075s sys 0m0.450s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case delaundo_PyTest.py passed (as expected) ================================================= Running.... CFD PyTests ================================================= + echo 'su2_and_AFLR2_NodeDist_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt su2_and_AFLR2_NodeDist_PyTest.py test; + python -u su2_and_AFLR2_NodeDist_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 224 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 224 224 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 46 94 AFLR2 IG : Nodes, Faces = 92 186 AFLR2 IG : Nodes, Faces = 138 278 AFLR2 IG : Nodes, Faces = 184 370 AFLR2 IG : Nodes, Faces = 196 394 AFLR2 IG : Nodes, Faces = 224 450 AFLR2 IG : Nodes, Faces = 228 450 AFLR2 IG : Nodes, Faces = 224 224 AFLR2 : CPU Time = 0.000 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 224 224 AFLR2 GG : Nodes, Faces = 440 656 AFLR2 GG : Nodes, Faces = 649 1074 AFLR2 GG : Nodes, Faces = 853 1482 AFLR2 GG : Nodes, Faces = 1050 1876 AFLR2 GG : Nodes, Faces = 1238 2252 AFLR2 GG : Nodes, Faces = 1421 2618 AFLR2 GG : Nodes, Faces = 1594 2964 AFLR2 GG : Nodes, Faces = 1760 3296 AFLR2 GG : Nodes, Faces = 1915 3606 AFLR2 GG : Nodes, Faces = 2063 3902 AFLR2 GG : Nodes, Faces = 2202 4180 AFLR2 GG : Nodes, Faces = 2314 4404 AFLR2 GG : Nodes, Faces = 2423 4622 AFLR2 GG : Nodes, Faces = 2528 4832 AFLR2 GG : Nodes, Faces = 2634 5044 AFLR2 GG : Nodes, Faces = 2732 5240 AFLR2 GG : Nodes, Faces = 2831 5438 AFLR2 GG : Nodes, Faces = 2927 5630 AFLR2 GG : Nodes, Faces = 3018 5812 AFLR2 GG : Nodes, Faces = 3109 5994 AFLR2 GG : Nodes, Faces = 3202 6180 AFLR2 GG : Nodes, Faces = 3295 6366 AFLR2 GG : Nodes, Faces = 3386 6548 AFLR2 GG : Nodes, Faces = 3464 6704 AFLR2 GG : Nodes, Faces = 3535 6846 AFLR2 GG : Nodes, Faces = 3594 6964 AFLR2 GG : Nodes, Faces = 3639 7054 AFLR2 GG : Nodes, Faces = 3671 7118 AFLR2 GG : Nodes, Faces = 3691 7158 AFLR2 GG : Nodes, Faces = 3705 7186 AFLR2 GG : Nodes, Faces = 3712 7200 AFLR2 GG : Nodes, Faces = 3715 7206 AFLR2 : CPU Time = 0.010 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 3715 7206 AFLR2 : CPU Time = 0.002 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 3715 Number of elements = 7430 Number of tris = 7206 Number of quad = 0 Writing SU2 file .... SU2 expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.4. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_5. Surface(s) plotted in the output file: BC_5, BC_2. Input mesh file name: ../aflr2/aflr2_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_SU2_aflr2.dat. Surface file name: surface_flow_pyCAPS_SU2_aflr2. Volume file name: flow_pyCAPS_SU2_aflr2. Restart file name: restart_flow_pyCAPS_SU2_aflr2.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Inlet boundary| BC_4| +-----------------------------------------------------------------------+ | Outlet boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Two dimensional problem. 3715 grid points. 7206 volume elements. 4 surface markers. 98 boundary elements in index 0 (Marker = BC_2). 24 boundary elements in index 1 (Marker = BC_3). 24 boundary elements in index 2 (Marker = BC_4). 78 boundary elements in index 3 (Marker = BC_5). 7206 triangles. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 7206 TRIANGLE volume elements. There has been a re-orientation of 73 LINE surface elements. Identifying edges and vertices. Setting the control volume structure. Area of the computational grid: 999.917. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 177.06. Mean K: 1.97231. Standard deviation K: 13.0434. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 63.4343| 90| | CV Face Area Aspect Ratio| 1| 5.23543| | CV Sub-Volume Ratio| 1| 3.11804| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 3715| 1/1.00| 10| | 1| 1048| 1/3.54| 7.96696| | 2| 298| 1/3.52| 6.37252| +-------------------------------------------+ Finding max control volume width. Wetted area = 2.06136 m. Area projection in the x-plane = 0.178383 m, y-plane = 0.994925 m. Max. coordinate in the x-direction = 1 m, y-direction = 0.138389 m. Min. coordinate in the x-direction = -0.000250564 m, y-direction = -0.0151999 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_5 is NOT a single straight. Boundary marker BC_2 is NOT a single straight. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 216054| 1| m^2/s^2| 216054| | Velocity-X| 136.119| 1| m/s| 136.119| | Velocity-Y| 0| 1| m/s| 0| | Velocity Magnitude| 136.119| 1| m/s| 136.119| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.4| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 4.3736e-02| -0.385358| 2.453598| 1.625650| 5.369499| 0.360138| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 4.3382e-02| -0.512634| 2.087781| 1.374671| 4.973554| 1.183036| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 4.1902e-02| -0.792582| 1.733529| 1.142729| 4.657622| 3.896320| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 4.2154e-02| -0.880738| 1.486539| 1.023158| 4.334759| 14.592265| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 4.2485e-02| -0.987528| 1.351478| 0.932491| 4.191092| 111.166022| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 4.2055e-02| -1.104038| 1.188715| 0.874764| 3.951825| -483.924340| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 4.1293e-02| -1.178622| 1.124587| 0.844310| 3.820426| 127.331200| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 4.1202e-02| -1.243517| 1.097463| 0.824869| 3.768858| 40.162273| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 4.1067e-02| -1.287932| 1.075843| 0.810639| 3.733440| 25.154653| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 4.0784e-02| -1.300689| 1.046363| 0.775886| 3.684245| 21.097801| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.30069| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_pyCAPS_SU2_aflr2.dat | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). |CSV file |surface_flow_pyCAPS_SU2_aflr2.csv | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). |Tecplot binary |flow_pyCAPS_SU2_aflr2.szplt | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). |Tecplot binary surface |surface_flow_pyCAPS_SU2_aflr2.szplt| Error in tecFileWriterClose: Not all node map values for zone 1 have been written. Currently need 352 more values.0: Error finishing Tecplot file output. Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.650457 Cd = 0.030831 Cmz = 0.373226 Cx = 0.030831 Cy = 0.650457 Pressure Contribution Cl_p = 0.650457 Cd_p = 0.030831 Cmz_p = 0.373226 Cx_p = 0.030831 Cy_p = 0.650457 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 real 0m3.609s user 0m1.730s sys 0m0.764s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_AFLR2_NodeDist_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_and_AFLR2_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt su2_and_AFLR2_PyTest.py test; + python -u su2_and_AFLR2_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Saving geometry Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 545 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 545 545 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 110 222 AFLR2 IG : Nodes, Faces = 220 442 AFLR2 IG : Nodes, Faces = 330 662 AFLR2 IG : Nodes, Faces = 440 882 AFLR2 IG : Nodes, Faces = 517 1036 AFLR2 IG : Nodes, Faces = 545 1092 AFLR2 IG : Nodes, Faces = 549 1092 AFLR2 IG : Nodes, Faces = 545 545 AFLR2 : CPU Time = 0.002 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GGp: Nodes, Faces = 545 545 AFLR2 GGp: Nodes, Faces = 1083 1621 AFLR2 GGp: Nodes, Faces = 1616 2687 AFLR2 GGp: Nodes, Faces = 2144 3743 AFLR2 GGp: Nodes, Faces = 2661 4777 AFLR2 GGp: Nodes, Faces = 3171 5797 AFLR2 GGp: Nodes, Faces = 3672 6799 AFLR2 GGp: Nodes, Faces = 4158 7771 AFLR2 GGp: Nodes, Faces = 4653 8761 AFLR2 GGp: Nodes, Faces = 5142 9739 AFLR2 GGp: Nodes, Faces = 5608 10671 AFLR2 GGp: Nodes, Faces = 6055 11565 AFLR2 GGp: Nodes, Faces = 6482 12419 AFLR2 GGp: Nodes, Faces = 6880 13215 AFLR2 GGp: Nodes, Faces = 7257 13969 AFLR2 GGp: Nodes, Faces = 7614 14683 AFLR2 GGp: Nodes, Faces = 7947 15349 AFLR2 GGp: Nodes, Faces = 8276 16007 AFLR2 GGp: Nodes, Faces = 8575 16605 AFLR2 GGp: Nodes, Faces = 8869 17193 AFLR2 GGp: Nodes, Faces = 9140 17735 AFLR2 GGp: Nodes, Faces = 9401 18257 AFLR2 GGp: Nodes, Faces = 9654 18763 AFLR2 GGp: Nodes, Faces = 9887 19229 AFLR2 GGp: Nodes, Faces = 10110 19675 AFLR2 GGp: Nodes, Faces = 10315 20085 AFLR2 GGp: Nodes, Faces = 10497 20449 AFLR2 GGp: Nodes, Faces = 10656 20767 AFLR2 GGp: Nodes, Faces = 10791 21037 AFLR2 GGp: Nodes, Faces = 10919 21293 AFLR2 GGp: Nodes, Faces = 11022 21499 AFLR2 GGp: Nodes, Faces = 11092 21639 AFLR2 GGp: Nodes, Faces = 11145 21745 AFLR2 GGp: Nodes, Faces = 11156 21767 AFLR2 : CPU Time = 0.049 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 11156 21767 AFLR2 QI : Nodes, Faces = 11155 819 AFLR2 QI : Nodes, Faces = 11155 10473 AFLR2 QI : Nodes, Faces = 11155 21765 AFLR2 QI : Nodes, Faces = 11154 811 AFLR2 QI : Nodes, Faces = 11154 10476 AFLR2 QI : Nodes, Faces = 11154 21763 AFLR2 QI : Nodes, Faces = 11154 805 AFLR2 QI : Nodes, Faces = 11154 10479 AFLR2 QI : Nodes, Faces = 11154 21763 AFLR2 QI : Nodes, Faces = 11154 911 AFLR2 QI : Nodes, Faces = 11154 10426 AFLR2 QI : Nodes, Faces = 11154 21763 AFLR2 QI : Nodes, Faces = 11153 915 AFLR2 QI : Nodes, Faces = 11153 10423 AFLR2 QI : Nodes, Faces = 11153 917 AFLR2 QI : Nodes, Faces = 11153 10423 AFLR2 : CPU Time = 0.019 seconds AFLR2 : DONE EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)! EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)! Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 11153 Number of elements = 11885 Number of tris = 917 Number of quad = 10423 EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)! EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)! EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)! EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)! Writing Tecplot file .... Tecplot expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing Tecplot file Writing SU2 file .... SU2 expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.4. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_5. Surface(s) plotted in the output file: BC_5, BC_2. Input mesh file name: ../aflr2/aflr2_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_su2_aflr2.dat. Surface file name: surface_flow_pyCAPS_su2_aflr2. Volume file name: flow_pyCAPS_su2_aflr2. Restart file name: restart_flow_pyCAPS_su2_aflr2.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Inlet boundary| BC_4| +-----------------------------------------------------------------------+ | Outlet boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Two dimensional problem. 11153 grid points. 11340 volume elements. 4 surface markers. 98 boundary elements in index 0 (Marker = BC_2). 24 boundary elements in index 1 (Marker = BC_3). 24 boundary elements in index 2 (Marker = BC_4). 399 boundary elements in index 3 (Marker = BC_5). 917 triangles. 10423 quadrilaterals. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 917 TRIANGLE volume elements. There has been a re-orientation of 10423 QUADRILATERAL volume elements. There has been a re-orientation of 73 LINE surface elements. Identifying edges and vertices. Setting the control volume structure. Area of the computational grid: 999.878. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 385.665. Mean K: 2.15881. Standard deviation K: 17.7215. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 49.3184| 90| | CV Face Area Aspect Ratio| 1.00035| 33.4982| | CV Sub-Volume Ratio| 1.00001| 7.89914| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11153| 1/1.00| 10| | 1| 2702| 1/4.13| 7.38309| | 2| 549| 1/4.92| 4.99198| +-------------------------------------------+ Finding max control volume width. Wetted area = 2.06265 m. Area projection in the x-plane = 0.211192 m, y-plane = 0.997011 m. Max. coordinate in the x-direction = 1 m, y-direction = 0.102037 m. Min. coordinate in the x-direction = 0.000323229 m, y-direction = -0.108492 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_5 is NOT a single straight. Boundary marker BC_2 is NOT a single straight. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 216054| 1| m^2/s^2| 216054| | Velocity-X| 136.119| 1| m/s| 136.119| | Velocity-Y| 0| 1| m/s| 0| | Velocity Magnitude| 136.119| 1| m/s| 136.119| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.4| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.2100e-01| 0.071067| 2.739763| 1.616077| 5.599701| 0.055267| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.1628e-01| -0.447576| 2.193837| 1.571349| 5.070382| 0.046028| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.1540e-01| -0.561159| 2.074597| 1.490746| 4.953698| 0.033910| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.1681e-01| -0.723326| 1.921155| 1.390756| 4.790278| 0.049695| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.1336e-01| -0.876572| 1.825653| 1.275093| 4.637161| 0.133976| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.1140e-01| -1.029177| 1.759196| 1.156078| 4.482282| 0.368542| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.0959e-01| -1.215334| 1.704909| 1.114966| 4.286060| 0.974759| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.0732e-01| -1.329970| 1.644937| 1.145030| 4.116982| 2.716332| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.0639e-01| -1.270672| 1.570739| 1.155400| 4.139480| 16.569216| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.0562e-01| -1.221243| 1.499646| 1.130319| 4.189559| -6.277653| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.22124| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_pyCAPS_su2_aflr2.dat | Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). |CSV file |surface_flow_pyCAPS_su2_aflr2.csv | Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). |Tecplot binary |flow_pyCAPS_su2_aflr2.szplt | Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). |Tecplot binary surface |surface_flow_pyCAPS_su2_aflr2.szplt| Error in tecFileWriterClose: Not all node map values for zone 1 have been written. Currently need 994 more values.0: Error finishing Tecplot file output. Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.072253 Cd = -0.01151 Cmz = 0.070975 Cx = -0.01151 Cy = 0.072253 Pressure Contribution Cl_p = 0.072253 Cd_p = -0.01151 Cmz_p = 0.070975 Cx_p = -0.01151 Cy_p = 0.072253 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 real 0m3.466s user 0m2.966s sys 0m0.822s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_AFLR2_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_and_AFLR4_AFLR3_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt su2_and_AFLR4_AFLR3_PyTest.py test; + python -u su2_and_AFLR4_AFLR3_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 39568 Number of elements = 228433 Number of triangles = 12446 Number of quadrilatarals = 0 Number of tetrahedrals = 215987 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wake Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.5901. Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 50 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 15.8114 m. Surface(s) where the force coefficients are evaluated and their reference origin for moment computation: - BC_1 (0, 0, 0). - BC_2 (0, 0, 0) m. Surface(s) plotted in the output file: BC_1, BC_2. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-8. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_su2AFLRTest.dat. Surface file name: surface_flow_su2AFLRTest. Volume file name: flow_su2AFLRTest. Restart file name: restart_flow_su2AFLRTest.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_4| +-----------------------------------------------------------------------+ | Internal boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 39568 grid points. 215987 volume elements. 4 surface markers. 6594 boundary elements in index 0 (Marker = BC_1). 5358 boundary elements in index 1 (Marker = BC_2). 74 boundary elements in index 2 (Marker = BC_3). 420 boundary elements in index 3 (Marker = BC_4). 215987 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.08667e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 4873.1. Mean K: 61.8682. Standard deviation K: 266.942. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 19.6996| 84.6456| | CV Face Area Aspect Ratio| 1.0296| 17700.2| | CV Sub-Volume Ratio| 1.04044| 328478| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 39568| 1/1.00| 10| | 1| 6515| 1/6.07| 8.22144| | 2| 1004| 1/6.49| 6.61169| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.90569 m. Wetted area = 118.038 m^2. Area projection in the x-plane = 11.1419 m^2, y-plane = 4.96714 m^2, z-plane = 55.4182 m^2. Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.582636 m. Min. coordinate in the x-direction = 0 m, y-direction = -7.90569 m, z-direction = -0.41192 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.2934e+00| -0.065995| 2.296266| 2.031890| 5.424900| 1.969324| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.2312e+00| -0.000146| 2.503192| 2.184653| 5.504433| 2.669994| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.2095e+00| 0.022836| 2.578793| 2.419949| 5.523561| 4.081575| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.2240e+00| -0.041097| 2.580097| 2.548191| 5.445039| 6.003651| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.2060e+00| -0.101756| 2.566392| 2.598258| 5.370190| 7.692754| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.2069e+00| -0.114949| 2.558251| 2.609841| 5.363328| 8.911043| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.2114e+00| -0.124738| 2.541827| 2.614192| 5.362516| 9.794574| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.2151e+00| -0.166905| 2.494151| 2.620861| 5.317920| 10.317284| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.2167e+00| -0.223036| 2.429312| 2.616363| 5.252496| 10.445731| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.2194e+00| -0.269524| 2.392168| 2.592960| 5.200595| 10.271172| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.269524| < -8| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_su2AFLRTest.dat | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |CSV file |surface_flow_su2AFLRTest.csv | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview |flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview surface |surface_flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.793167 Cd = 0.077223 Cmx = 4.2e-05 Cmy = -0.202205 Cmz = -7.7e-05 Cx = 0.063368 Cy = 0.000296 Cz = 0.794394 Pressure Contribution Cl_p = 0.793167 Cd_p = 0.077223 Cmx_p = 4.2e-05 Cmy_p = -0.202205 Cmz_p = -7.7e-05 Cx_p = 0.063368 Cy_p = 0.000296 Cz_p = 0.794394 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmx_v = 0.0 Cmy_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 Cz_v = 0.0 real 0m40.413s user 0m38.451s sys 0m1.589s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_AFLR4_AFLR3_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_Morph_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt su2_Morph_PyTest.py test; + python -u su2_Morph_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 56157 Number of elements = 325507 Number of triangles = 15872 Number of quadrilatarals = 0 Number of tetrahedrals = 309635 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wake Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Writing SU2 surface file Writing SU2 Motion File - su2AFLRTest_motion.dat Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 15 - bcProps.surfaceProp[2].surfaceType = 1 - bcProps.surfaceProp[3].surfaceType = 1 Done boundary flags Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.5901. Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 40 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 14.1421 m. Surface(s) where the force coefficients are evaluated and their reference origin for moment computation: - BC_1 (0, 0, 0). - BC_2 (0, 0, 0) m. Surface(s) plotted in the output file: BC_1, BC_2. Surface(s) affected by the design variables: BC_1, BC_2. Input mesh file name: ../volumeMesh/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-8. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_su2AFLRTest.dat. Surface file name: surface_flow_su2AFLRTest. Volume file name: flow_su2AFLRTest. Restart file name: restart_flow_su2AFLRTest.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_4| +-----------------------------------------------------------------------+ | Internal boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 56157 grid points. 309635 volume elements. 4 surface markers. 9958 boundary elements in index 0 (Marker = BC_1). 5414 boundary elements in index 1 (Marker = BC_2). 80 boundary elements in index 2 (Marker = BC_3). 420 boundary elements in index 3 (Marker = BC_4). 309635 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.08667e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 5523.74. Mean K: 58.8177. Standard deviation K: 282.533. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 22.8021| 84.7788| | CV Face Area Aspect Ratio| 1.00879| 391253| | CV Sub-Volume Ratio| 1.03553| 1.49697e+06| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 56157| 1/1.00| 10| | 1| 9189| 1/6.11| 8.20439| | 2| 1395| 1/6.59| 6.56507| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.07107 m. Wetted area = 96.2324 m^2. Area projection in the x-plane = 7.65774 m^2, y-plane = 4.21853 m^2, z-plane = 45.5887 m^2. Max. coordinate in the x-direction = 12.3872 m, y-direction = 7.07107 m, z-direction = 0.521791 m. Min. coordinate in the x-direction = 0 m, y-direction = -7.07107 m, z-direction = -0.0650201 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.9005e+00| -0.458238| 1.872911| 1.656342| 5.032658| 0.747356| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.8286e+00| -0.474495| 2.012416| 1.722531| 5.023251| 1.417645| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.8110e+00| -0.411436| 2.112682| 1.938918| 5.080139| 3.206640| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.8040e+00| -0.401624| 2.160654| 2.076942| 5.079456| 6.873640| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.8004e+00| -0.411670| 2.180863| 2.151230| 5.057111| 12.470424| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.8001e+00| -0.425533| 2.184395| 2.189878| 5.041713| 19.530915| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.7823e+00| -0.436222| 2.170558| 2.217712| 5.036784| 27.444937| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.7673e+00| -0.438251| 2.130034| 2.242936| 5.037249| 32.489152| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.7569e+00| -0.443916| 2.073807| 2.259407| 5.025917| 31.208484| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.7500e+00| -0.475232| 2.015341| 2.254570| 4.986738| 26.459437| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.475232| < -8| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_su2AFLRTest.dat | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |CSV file |surface_flow_su2AFLRTest.csv | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview |flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview surface |surface_flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.521992 Cd = 0.019728 Projecting tessellation 1 (of 4) on to new body Projecting tessellation 2 (of 4) on to new body Projecting tessellation 3 (of 4) on to new body Projecting tessellation 4 (of 4) on to new body Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wake Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Writing SU2 surface file Writing SU2 Motion File - su2AFLRTest_motion.dat Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 15 - bcProps.surfaceProp[2].surfaceType = 1 - bcProps.surfaceProp[3].surfaceType = 1 Done boundary flags Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Mesh Morphing...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_4| +-----------------------------------------------------------------------+ | Internal boundary| BC_3| +-----------------------------------------------------------------------+ Three dimensional problem. 56157 grid points. 309635 volume elements. 4 surface markers. 9958 boundary elements in index 0 (Marker = BC_1). 5414 boundary elements in index 1 (Marker = BC_2). 80 boundary elements in index 2 (Marker = BC_3). 420 boundary elements in index 3 (Marker = BC_4). 309635 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 2.08667e+06. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Ignoring Convergence Field(s): RMS_DENSITY Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 10.819008 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Paraview |volume_deformed.vtu | |Paraview surface |surface_deformed.vtu | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.5901. Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 40 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 14.1421 m. Surface(s) where the force coefficients are evaluated and their reference origin for moment computation: - BC_1 (0, 0, 0). - BC_2 (0, 0, 0) m. Surface(s) plotted in the output file: BC_1, BC_2. Surface(s) affected by the design variables: BC_1, BC_2. Input mesh file name: aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-8. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_su2AFLRTest.dat. Surface file name: surface_flow_su2AFLRTest. Volume file name: flow_su2AFLRTest. Restart file name: restart_flow_su2AFLRTest.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_4| +-----------------------------------------------------------------------+ | Internal boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 56157 grid points. 309635 volume elements. 4 surface markers. 9958 boundary elements in index 0 (Marker = BC_1). 5414 boundary elements in index 1 (Marker = BC_2). 80 boundary elements in index 2 (Marker = BC_3). 420 boundary elements in index 3 (Marker = BC_4). 309635 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.08667e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 5523.56. Mean K: 58.7619. Standard deviation K: 282.437. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 22.4386| 85.0504| | CV Face Area Aspect Ratio| 1.03872| 385864| | CV Sub-Volume Ratio| 1.04173| 1.51643e+06| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 56157| 1/1.00| 10| | 1| 9189| 1/6.11| 8.20439| | 2| 1395| 1/6.59| 6.56507| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.07107 m. Wetted area = 95.6308 m^2. Area projection in the x-plane = 9.17945 m^2, y-plane = 4.04295 m^2, z-plane = 44.962 m^2. Max. coordinate in the x-direction = 12.3585 m, y-direction = 7.07107 m, z-direction = 0.521791 m. Min. coordinate in the x-direction = 0 m, y-direction = -7.07107 m, z-direction = -0.400127 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 2.0214e+00| -0.397716| 1.978508| 1.645118| 5.093179| 1.915087| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.0393e+00| -0.257369| 2.241094| 1.916257| 5.249805| 2.557622| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.9455e+00| -0.191638| 2.350399| 2.185809| 5.310465| 3.925162| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.9101e+00| -0.217261| 2.380880| 2.338313| 5.269941| 5.872036| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.8770e+00| -0.261506| 2.381321| 2.406007| 5.209923| 7.749274| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.8426e+00| -0.289071| 2.378299| 2.432486| 5.189120| 9.267784| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.8160e+00| -0.307559| 2.365345| 2.449297| 5.186812| 10.504429| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.8870e+00| -0.325707| 2.326921| 2.468701| 5.171814| 11.399364| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.8700e+00| -0.348872| 2.267332| 2.478078| 5.139102| 11.874957| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.8522e+00| -0.386484| 2.208640| 2.465734| 5.091093| 11.956189| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.386484| < -8| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_su2AFLRTest.dat | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |CSV file |surface_flow_su2AFLRTest.csv | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview |flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview surface |surface_flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.884829 Cd = 0.074006 real 1m21.871s user 1m14.392s sys 0m6.297s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_Morph_PyTest.py passed (as expected) ================================================= delaundo: /Users/jenkins/util/delaundo/delaundo/src/delaundo ================================================= + echo 'su2_and_Delaundo_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt su2_and_Delaundo_PyTest.py test; + python -u su2_and_Delaundo_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting edge discretization for body 1 Delaundo expects 2D meshes in the x-y plane... attempting to rotate mesh through node swapping! Swapping z and y coordinates! Writing delaundo control file - delaundo.ctr Writing out *.pts file Reading delaundo mesh file - delaundo_CAPS.mesh Swapping y and z coordinates! Writing Tecplot file .... Tecplot expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing Tecplot file Writing SU2 file .... SU2 expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Warning: No boundary condition specified for capsGroup 2DSlice! Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.4. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_5. Surface(s) plotted in the output file: BC_5, BC_2. Input mesh file name: ../delaundo/delaundo_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_su2_CAPS.dat. Surface file name: surface_flow_su2_CAPS. Volume file name: flow_su2_CAPS. Restart file name: restart_flow_su2_CAPS.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Inlet boundary| BC_4| +-----------------------------------------------------------------------+ | Outlet boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Two dimensional problem. 6320 grid points. 12346 volume elements. 5 surface markers. 24 boundary elements in index 0 (Marker = BC_2). 24 boundary elements in index 1 (Marker = BC_3). 24 boundary elements in index 2 (Marker = BC_2). 24 boundary elements in index 3 (Marker = BC_4). 198 boundary elements in index 4 (Marker = BC_5). 12346 triangles. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. There has been a re-orientation of 294 LINE surface elements. Identifying edges and vertices. Setting the control volume structure. Area of the computational grid: 999.917. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 1792.95. Mean K: 10.8142. Standard deviation K: 104.33. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 45.3524| 89.3051| | CV Face Area Aspect Ratio| 1.0235| 15.7138| | CV Sub-Volume Ratio| 1| 7.93643| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 6320| 1/1.00| 10| | 1| 1790| 1/3.53| 7.98287| | 2| 504| 1/3.55| 6.35388| +-------------------------------------------+ Finding max control volume width. Wetted area = 2.07206 m. Area projection in the x-plane = 0.179342 m, y-plane = 1.00053 m. Max. coordinate in the x-direction = 1 m, y-direction = 0.138492 m. Min. coordinate in the x-direction = -0.00104578 m, y-direction = -0.0151891 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_5 is NOT a single straight. Boundary marker BC_2 is a single straight. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 216054| 1| m^2/s^2| 216054| | Velocity-X| 136.119| 1| m/s| 136.119| | Velocity-Y| 0| 1| m/s| 0| | Velocity Magnitude| 136.119| 1| m/s| 136.119| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.4| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 8.1224e-02| -1.163171| 1.073770| 1.341444| 4.312165| 0.062120| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 7.3536e-02| -1.561828| 0.808636| 0.967487| 3.922716| 0.139775| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 7.2965e-02| -1.601698| 0.943793| 1.009036| 3.876382| 0.373708| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 7.4475e-02| -1.659374| 1.008221| 1.015635| 3.799753| 0.952935| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 7.2689e-02| -1.663585| 1.011627| 0.956487| 3.788246| 2.344781| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 7.3104e-02| -1.633451| 0.991734| 0.872954| 3.829708| 6.259549| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 7.1609e-02| -1.626398| 0.990123| 0.847075| 3.843511| 26.349556| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 7.1390e-02| -1.643439| 1.009125| 0.895796| 3.825758| -56.104876| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 7.2176e-02| -1.659565| 1.020774| 0.939260| 3.804303| -24.431167| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 7.1876e-02| -1.676757| 1.012633| 0.938320| 3.783310| -21.456835| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.67676| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_su2_CAPS.dat | Writing the forces breakdown file (forces_breakdown_su2_CAPS.dat). |CSV file |surface_flow_su2_CAPS.csv | Writing the forces breakdown file (forces_breakdown_su2_CAPS.dat). |Tecplot binary |flow_su2_CAPS.szplt | Writing the forces breakdown file (forces_breakdown_su2_CAPS.dat). |Tecplot binary surface |surface_flow_su2_CAPS.szplt | Error in tecFileWriterClose: Not all node map values for zone 1 have been written. Currently need 492 more values.0: Error finishing Tecplot file output. Writing the forces breakdown file (forces_breakdown_su2_CAPS.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.805231 Cd = -0.037528 Cmz = 0.414714 Cx = -0.037528 Cy = 0.805231 Pressure Contribution Cl_p = 0.805231 Cd_p = -0.037528 Cmz_p = 0.414714 Cx_p = -0.037528 Cy_p = 0.805231 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 real 0m2.690s user 0m2.246s sys 0m0.798s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_Delaundo_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_and_Tetgen_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt su2_and_Tetgen_PyTest.py test; + python -u su2_and_Tetgen_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 2236 Number of elements = 4468 Number of triangle elements = 4468 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 636 Number of elements = 1268 Number of triangle elements = 1268 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 267 Number of elements = 530 Number of triangle elements = 530 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3139 Total number of elements = 6266 Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 3139, elements - 6266 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.024792 Creating surface mesh ... Surface mesh seconds: 0.007348 Recovering boundaries... Boundary recovery seconds: 0.079275 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.00869 Suppressing Steiner points ... Steiner suppression seconds: 5.6e-05 Recovering Delaunayness... Delaunay recovery seconds: 0.013606 Refining mesh... 4189 insertions, added 2138 points, 127097 tetrahedra in queue. 1394 insertions, added 409 points, 130640 tetrahedra in queue. 1859 insertions, added 449 points, 127916 tetrahedra in queue. 2478 insertions, added 473 points, 111923 tetrahedra in queue. 3303 insertions, added 484 points, 65315 tetrahedra in queue. 4403 insertions, added 433 points, 571 tetrahedra in queue. Refinement seconds: 0.737348 Smoothing vertices... Mesh smoothing seconds: 0.495537 Improving mesh... Mesh improvement seconds: 0.012613 Jettisoning redundant points. Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.00308 Total running seconds: 1.38291 Statistics: Input points: 3139 Input facets: 6266 Input segments: 9399 Input holes: 2 Input regions: 0 Mesh points: 8039 Mesh tetrahedra: 39668 Mesh faces: 82470 Mesh faces on exterior boundary: 6268 Mesh faces on input facets: 6268 Mesh edges on input segments: 9400 Steiner points on input segments: 1 Steiner points inside domain: 4899 Done meshing using TetGen! Volume mesher did not preserve surface elements - data transfer will NOT be possible. Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.5901. Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 50 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 15.8114 m. Surface(s) where the force coefficients are evaluated and their reference origin for moment computation: - BC_1 (0, 0, 0). - BC_2 (0, 0, 0) m. Surface(s) plotted in the output file: BC_1, BC_2. Input mesh file name: ../myMesh/tetgen_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_SU2_Tetgen.dat. Surface file name: surface_flow_pyCAPS_SU2_Tetgen. Volume file name: flow_pyCAPS_SU2_Tetgen. Restart file name: restart_flow_pyCAPS_SU2_Tetgen.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 8039 grid points. 39668 volume elements. 3 surface markers. 4468 boundary elements in index 0 (Marker = BC_1). 1270 boundary elements in index 1 (Marker = BC_2). 530 boundary elements in index 2 (Marker = BC_3). 39668 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.08934e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 414.134. Mean K: 30.561. Standard deviation K: 37.5336. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 1.83144| 84.8022| | CV Face Area Aspect Ratio| 1.55015| 7101.39| | CV Sub-Volume Ratio| 1.05639| 198266| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 8039| 1/1.00| 10| | 1| 1338| 1/6.01| 8.25105| | 2| 214| 1/6.25| 6.7182| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.90569 m. Wetted area = 120.046 m^2. Area projection in the x-plane = 10.7914 m^2, y-plane = 4.58502 m^2, z-plane = 57.287 m^2. Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.557773 m. Min. coordinate in the x-direction = -0.00409054 m, y-direction = -7.90569 m, z-direction = -0.41192 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 2.2532e-01| 0.619384| 3.051344| 2.094590| 6.110279| 1.812161| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.1195e-01| 0.785542| 3.264371| 2.974872| 6.285549| 2.181906| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.0889e-01| 0.724139| 3.334285| 3.249736| 6.229534| 3.226648| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 2.0490e-01| 0.621976| 3.305627| 3.334988| 6.113861| 4.648342| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.0609e-01| 0.625390| 3.207240| 3.303991| 6.098630| 5.785533| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 0.62539| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_pyCAPS_SU2_Tetgen.dat | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat). |CSV file |surface_flow_pyCAPS_SU2_Tetgen.csv | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat). |Paraview |flow_pyCAPS_SU2_Tetgen.vtu | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat). |Paraview surface |surface_flow_pyCAPS_SU2_Tetgen.vtu | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.759441 Cd = 0.131266 Cmx = 0.001646 Cmy = -0.215157 Cmz = 0.000487 Cx = 0.117991 Cy = 0.00137 Cz = 0.761616 real 1m2.728s user 1m1.817s sys 0m1.123s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_Tetgen_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_X43a_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt su2_X43a_PyTest.py test; + python -u su2_X43a_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = fuselage, index = 1 Name = verticalCS, index = 2 Name = fuselage_base, index = 3 Name = horizontalCS, index = 4 Name = inlet, index = 5 Name = hollowInlet, index = 6 Name = Farfield, index = 7 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 3808 Number of elements = 7616 Number of triangle elements = 7616 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 5654 Number of elements = 11304 Number of triangle elements = 11304 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 9462 Total number of elements = 18920 Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = fuselage, index = 1 Name = verticalCS, index = 2 Name = fuselage_base, index = 3 Name = horizontalCS, index = 4 Name = inlet, index = 5 Name = hollowInlet, index = 6 Name = Farfield, index = 7 Number of surface: nodes - 9462, elements - 18920 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.082233 Creating surface mesh ... Surface mesh seconds: 0.024667 Recovering boundaries... Warning: 6 segments are not recovered. Boundary recovery seconds: 0.23738 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.020335 Suppressing Steiner points ... Steiner suppression seconds: 6.7e-05 Recovering Delaunayness... Delaunay recovery seconds: 0.031399 Refining mesh... 12616 insertions, added 5206 points, 8134 tetrahedra in queue. Refinement seconds: 1.00884 Smoothing vertices... Mesh smoothing seconds: 0.67282 Improving mesh... Mesh improvement seconds: 0.023638 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.009228 Total running seconds: 2.11603 Statistics: Input points: 9462 Input facets: 18920 Input segments: 28380 Input holes: 6 Input regions: 0 Mesh points: 14813 Mesh tetrahedra: 61044 Mesh faces: 131551 Mesh faces on exterior boundary: 18926 Mesh faces on input facets: 18926 Mesh edges on input segments: 28383 Steiner points on input segments: 3 Steiner points inside domain: 5348 Done meshing using TetGen! Volume mesher did not preserve surface elements - data transfer will NOT be possible. Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - fuselage Boundary condition name - fuselage_base Boundary condition name - hollowInlet Boundary condition name - horizontalCS Boundary condition name - inlet Boundary condition name - verticalCS Done getting CFD boundary conditions Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 1 - bcProps.surfaceProp[2].surfaceType = 1 - bcProps.surfaceProp[3].surfaceType = 1 - bcProps.surfaceProp[4].surfaceType = 1 - bcProps.surfaceProp[5].surfaceType = 1 - bcProps.surfaceProp[6].surfaceType = 1 Done boundary flags Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 3.5. Angle of attack (AoA): 3 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Surface(s) where the force coefficients are evaluated and their reference origin for moment computation: - BC_1 (0, 0, 0). - BC_3 (0, 0, 0). - BC_4 (0, 0, 0). - BC_2 (0, 0, 0). - BC_5 (0, 0, 0). - BC_6 (0, 0, 0) m. Surface(s) plotted in the output file: BC_1, BC_3, BC_6, BC_4, BC_5, BC_2. Input mesh file name: ../myMesh/tetgen_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_x43a_Test.dat. Surface file name: surface_flow_x43a_Test. Volume file name: flow_x43a_Test. Restart file name: restart_flow_x43a_Test.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_3| | | BC_6| | | BC_4| | | BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_7| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 14813 grid points. 61044 volume elements. 7 surface markers. 4460 boundary elements in index 0 (Marker = BC_1). 1686 boundary elements in index 1 (Marker = BC_2). 92 boundary elements in index 2 (Marker = BC_3). 696 boundary elements in index 3 (Marker = BC_4). 436 boundary elements in index 4 (Marker = BC_5). 252 boundary elements in index 5 (Marker = BC_6). 11304 boundary elements in index 6 (Marker = BC_7). 61044 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.67744e+08. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 95.6599. Mean K: 0.658518. Standard deviation K: 2.74782. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 1.759| 83.6683| | CV Face Area Aspect Ratio| 1.80563| 60514.2| | CV Sub-Volume Ratio| 1| 8.7549e+08| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 14813| 1/1.00| 10| | 1| 2926| 1/5.06| 8.73578| | 2| 763| 1/3.83| 8.37162| +-------------------------------------------+ Finding max control volume width. Semi-span length = 30 m. Wetted area = 13761.9 m^2. Area projection in the x-plane = 776.902 m^2, y-plane = 2106.77 m^2, z-plane = 5468.8 m^2. Max. coordinate in the x-direction = 150 m, y-direction = 30 m, z-direction = 19 m. Min. coordinate in the x-direction = 0 m, y-direction = -30 m, z-direction = -10.3 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_3 is a single plane. Boundary marker BC_6 is NOT a single plane. Boundary marker BC_4 is NOT a single plane. Boundary marker BC_5 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 916077| 1| m^2/s^2| 916077| | Velocity-X| 1189.41| 1| m/s| 1189.41| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 62.3342| 1| m/s| 62.3342| | Velocity Magnitude| 1191.04| 1| m/s| 1191.04| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 3.5| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 4.3704e-01| 2.731919| 5.652900| 4.718102| 8.731395| -0.522472| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 4.1694e-01| 3.167847| 6.259056| 5.768590| 9.150983| -0.139661| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 4.2097e-01| 3.287831| 6.387102| 5.862744| 9.254034| -0.051712| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 4.3635e-01| 3.239493| 6.328939| 5.747105| 9.239192| -0.091054| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 4.4744e-01| 3.139807| 6.198963| 5.587302| 9.124785| -0.155781| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 3.13981| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_x43a_Test.dat | Writing the forces breakdown file (forces_breakdown_x43a_Test.dat). |CSV file |surface_flow_x43a_Test.csv | Writing the forces breakdown file (forces_breakdown_x43a_Test.dat). |Paraview |flow_x43a_Test.vtu | Writing the forces breakdown file (forces_breakdown_x43a_Test.dat). |Paraview surface |surface_flow_x43a_Test.vtu | Writing the forces breakdown file (forces_breakdown_x43a_Test.dat). +-----------------------------------------------------------------------+ Warning: there are 213 non-physical points in the solution. Warning: 94 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = -15.349382 Cd = 98.531638 Cmx = -27.598823 Cmy = 10655.287295 Cmz = -206.849785 Cx = 99.199929 Cy = -2.371531 Cz = -10.171598 real 0m13.064s user 0m14.781s sys 0m1.400s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_X43a_PyTest.py passed (as expected) ================================================= ================================================= + echo 'fun3d_Morph_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt fun3d_Morph_PyTest.py test; + python -u fun3d_Morph_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 83038 Number of elements = 484451 Number of triangles = 15680 Number of quadrilatarals = 0 Number of tetrahedrals = 468771 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Getting CFD design variables....... Number of design variables - 2 Design Variable name - Alpha Design Variable name - twist Done getting CFD design variables Getting CFD functional....... Number of design variables - 2 Objective name - Cd2 Objective name - Const Done getting CFD functional Python library was linked, but will not be used! Creating FUN3D directory tree DesignVariable = Alpha DesignVariable = twist Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1 Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1 Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1 Writing rubber.data Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Reading rubber.data Projecting tessellation 1 (of 3) on to new body Projecting tessellation 2 (of 3) on to new body Projecting tessellation 3 (of 3) on to new body Python library was linked, but will not be used! Creating FUN3D directory tree DesignVariable = Alpha DesignVariable = twist Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1 Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1 Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1 Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Reading rubber.data real 0m16.618s user 0m14.968s sys 0m1.369s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case fun3d_Morph_PyTest.py passed (as expected) ================================================= Running.... STRUCTURE PyTests ================================================= + echo 'masstran_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt masstran_PyTest.py test; + python -u masstran_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Getting results mass properties..... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Ribs_and_Spars, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 1159 Number of elements = 798 Number of triangle elements = 0 Number of quadrilateral elements = 798 ---------------------------- Total number of nodes = 1159 Total number of elements = 798 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Constraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Ribs_and_Spars, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1159 Number of elements = 798 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 798 Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - Ribs_and_Spars No "material" specified for Property tuple Ribs_and_Spars, defaulting to an index of 1 Done getting FEA properties Updating mesh element types based on properties input Area 3.428666259747 Mass 5383.006027803 Centroid [1.222256036874, 0.1634981473778, -4.234492548615e-11] CG [1.222256036874, 0.1634981473778, -4.234574416087e-11] Ixx 22133.97306033 Iyy 23448.30046709 Izz 1389.213122582 Ixy 164.2055275657 Ixz -7.454849830627e-06 Iyz 1.707682983295e-06 I [22133.97306033, 23448.30046709, 1389.213122582, 164.2055275657, -7.454849830627e-06, 1.707682983295e-06] II [[22133.97306033, -164.2055275657, 7.454849830627e-06], [-164.2055275657, 23448.30046709, -1.707682983295e-06], [7.454849830627e-06, -1.707682983295e-06, 1389.213122582]] real 0m7.568s user 0m10.369s sys 0m2.618s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case masstran_PyTest.py passed (as expected) ================================================= ================================================= + echo 'masstran_AGARD445_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt masstran_AGARD445_PyTest.py test; + python -u masstran_AGARD445_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Getting results mass properties..... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = constEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = yatesPlate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 36 Number of elements = 25 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 25 Getting FEA materials....... Number of materials - 1 Material name - Mahogany Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - yatesPlate Done getting FEA properties Updating mesh element types based on properties input Area 547.7004 Mass 0.01605224431138 Centroid [20.03586282449, 14.01686746988, 0.0] CG [20.03586282449, 14.01686746988, 0.0] Ixx 1.140246300554 Iyy 0.919317482675 Izz 2.059563783229 Ixy 0.7352134614013 Ixz 0.0 Iyz 0.0 I [1.140246300554, 0.919317482675, 2.059563783229, 0.7352134614013, 0.0, 0.0] II [[1.140246300554, -0.7352134614013, -0.0], [-0.7352134614013, 0.919317482675, -0.0], [-0.0, -0.0, 2.059563783229]] real 0m1.016s user 0m0.848s sys 0m0.284s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case masstran_AGARD445_PyTest.py passed (as expected) ================================================= ================================================= + echo 'hsm_SingleLoadCase_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt hsm_SingleLoadCase_PyTest.py test; + python -u hsm_SingleLoadCase_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plate, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Creating HSM BEM Getting quads for BEM! Number of nodal coordinates = 81 Number of elements = 96 Elemental Tria3 = 0 Elemental Quad4 = 64 Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA loads....... Number of loads - 1 Load name - appliedPressure Done getting FEA loads Writing Nastran grid and connectivity file (in small field format) .... Finished writing Nastran grid file Max Adjacency set to = 9 MaxDim = 32, numBCEdge = 0, numBCNode = 32, numJoint = 0 NEED TO ADD MORE CODE TO hsm_setGlobalParameter NEED TO ADD MORE CODE TO hsm_setNodeBCParameter NumBCNode = 32 ->HSMSOL Matrix Non-zero Entries = 5741 Converging HSM equation system ... iter dr dd dp rlx max 1 0.130E-01 0.165E+00 0.153E-04 1.000 ddy @ ( 0.25 0.06 0.00) 1* 0.260E-03 0.000E+00 0.000E+00 1.000 drz @ ( 0.25 0.12 0.00) 1* 0.240E-05 0.000E+00 0.000E+00 1.000 drz @ ( 0.25 0.09 0.00) 2 0.379E-02 0.505E-01 0.750E-04 1.000 ddy @ ( 0.25 0.19 0.00) 2* 0.420E-04 0.000E+00 0.000E+00 1.000 drz @ ( 0.25 0.12 0.00) 3 0.168E-02 0.225E-01 0.208E-04 1.000 ddy @ ( 0.25 0.06 0.00) 4 0.325E-03 0.427E-02 0.250E-05 1.000 ddy @ ( 0.25 0.19 0.00) 5 0.794E-05 0.112E-03 0.170E-06 1.000 ddy @ ( 0.25 0.19 0.00) 6 0.387E-08 0.598E-07 0.197E-09 1.000 ddy @ ( 0.25 0.06 0.00) 7 0.848E-15 0.147E-13 0.924E-15 1.000 ddy @ ( 0.25 0.19 0.00) Converging n vectors ... it = 1 dn = 0.788E-01 rlx = 1.000 ( 59 ) it = 2 dn = 0.566E-16 rlx = 1.000 ( 35 ) Converging e1,e2 vectors ... it = 1 de = 0.691E-03 rlx = 1.000 ( 45 ) it = 2 de = 0.404E-04 rlx = 1.000 ( 9 ) it = 3 de = 0.142E-07 rlx = 1.000 ( 46 ) it = 4 de = 0.521E-11 rlx = 1.000 ( 62 ) Calculating strains, stress resultants ... Writing HSM solution to Tecplot File - HSMSingleLoadPlate.dat real 0m1.475s user 0m1.329s sys 0m0.199s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case hsm_SingleLoadCase_PyTest.py passed (as expected) ================================================= ================================================= + echo 'hsm_CantileverPlate_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt hsm_CantileverPlate_PyTest.py test; + python -u hsm_CantileverPlate_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping Csys attributes ................ Number of unique Csys attributes = 1 Name = plate, index = 1 Getting FEA coordinate systems....... Number of coordinate systems - 1 Coordinate system name - plate Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plateTip, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Creating HSM BEM Getting quads for BEM! Number of nodal coordinates = 40 Number of elements = 51 Elemental Tria3 = 0 Elemental Quad4 = 27 Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA loads....... Number of loads - 1 Load name - appliedLoad Done getting FEA loads Writing Nastran grid and connectivity file (in small field format) .... Finished writing Nastran grid file Max Adjacency set to = 9 MaxDim = 4, numBCEdge = 3, numBCNode = 4, numJoint = 0 NEED TO ADD MORE CODE TO hsm_setGlobalParameter NEED TO ADD MORE CODE TO hsm_setNodeBCParameter NumBCNode = 4 ->HSMSOL Matrix Non-zero Entries = 1313 Converging HSM equation system ... iter dr dd dp rlx max 1 0.314E+01 0.628E+01 0.000E+00 0.080 ddx @ ( 1.00 0.00 0.00) 1* 0.341E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 1* 0.326E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.03 0.00) 1* 0.438E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 2 0.274E+01 0.521E+01 0.106E-07 0.096 ddx @ ( 1.00 0.03 0.00) 2* 0.321E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 2* 0.373E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.07 0.00) 2* 0.777E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.07 0.00) 3 0.202E+01 0.439E+01 0.928E-07 0.114 ddz @ ( 1.00 0.03 0.00) 3* 0.442E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.07 0.00) 3* 0.623E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.07 0.00) 3* 0.163E-03 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.07 0.00) 3* 0.167E-06 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 4 0.192E+01 0.476E+01 0.126E-07 0.105 ddz @ ( 1.00 0.03 0.00) 4* 0.335E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 4* 0.332E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 4* 0.451E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 5 0.187E+01 0.394E+01 0.254E-07 0.127 ddz @ ( 1.00 0.07 0.00) 5* 0.353E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 5* 0.379E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 5* 0.638E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 6 0.156E+01 0.300E+01 0.112E-06 0.166 ddx @ ( 1.00 0.03 0.00) 6* 0.326E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 6* 0.575E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 6* 0.193E-03 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 6* 0.272E-06 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 7 0.103E+01 0.323E+01 0.345E-07 0.155 ddx @ ( 1.00 0.03 0.00) 7* 0.259E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 7* 0.297E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 7* 0.435E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.10 0.00) 8 0.756E+00 0.259E+01 0.139E-07 0.193 ddx @ ( 1.00 0.07 0.00) 8* 0.295E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 8* 0.350E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 8* 0.587E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 9 0.678E+00 0.179E+01 0.639E-07 0.279 ddx @ ( 0.89 0.10 0.00) 9* 0.330E-01 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 9* 0.457E-02 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 9* 0.167E-03 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 9* 0.264E-06 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 10 0.452E+00 0.171E+01 0.499E-07 0.292 ddz @ ( 1.00 0.00 0.00) 10* 0.166E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 10* 0.239E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) 10* 0.393E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.10 0.00) iter dr dd dp rlx max 11 0.257E+00 0.120E+01 0.614E-08 0.417 ddz @ ( 1.00 0.10 0.00) 11* 0.206E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 11* 0.283E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 11* 0.488E-04 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 12 0.131E+00 0.647E+00 0.288E-08 0.772 ddz @ ( 0.89 0.10 0.00) 12* 0.238E-01 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 12* 0.357E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 12* 0.849E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 13 0.393E-01 0.238E+00 0.325E-07 1.000 ddx @ ( 1.00 0.03 0.00) 13* 0.336E-02 0.000E+00 0.000E+00 1.000 drz @ ( 1.00 0.00 0.00) 13* 0.936E-04 0.000E+00 0.000E+00 1.000 drx @ ( 1.00 0.00 0.00) 14 0.475E-03 0.514E-02 0.635E-07 1.000 ddx @ ( 1.00 0.00 0.00) 15 0.893E-06 0.651E-06 0.135E-08 1.000 drx @ ( 1.00 0.10 0.00) 16 0.574E-10 0.216E-09 0.140E-11 1.000 ddx @ ( 0.44 0.10 0.00) 17 0.558E-15 0.304E-14 0.603E-15 1.000 ddx @ ( 1.00 0.00 0.00) Converging n vectors ... it = 1 dn = 0.193E+01 rlx = 1.000 ( 12 ) it = 2 dn = 0.435E-15 rlx = 1.000 ( 28 ) Converging e1,e2 vectors ... it = 1 de = 0.285E+01 rlx = 0.351 ( 24 ) it = 2 de = 0.292E+01 rlx = 0.342 ( 34 ) it = 3 de = 0.226E+01 rlx = 0.442 ( 34 ) it = 4 de = 0.151E+01 rlx = 0.660 ( 34 ) it = 5 de = 0.665E+00 rlx = 1.000 ( 34 ) it = 6 de = 0.609E-01 rlx = 1.000 ( 34 ) it = 7 de = 0.573E-04 rlx = 1.000 ( 34 ) it = 8 de = 0.478E-13 rlx = 1.000 ( 34 ) Calculating strains, stress resultants ... Writing HSM solution to Tecplot File - HSMCantileverPlate.dat real 0m1.211s user 0m1.118s sys 0m0.215s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case hsm_CantileverPlate_PyTest.py passed (as expected) ================================================= ASTROS_ROOT: /Users/jenkins/util/astros/Astros/Darwin-64bit ================================================= + echo 'astros_Aeroelastic_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_Aeroelastic_PyTest.py test; + python -u astros_Aeroelastic_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root_Point, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = Skin_Top, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = Rib_Root, index = 1 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 1 Name = Rib_Root_Point, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = Ribs, index = 1 Name = Skin, index = 2 Name = Spar1, index = 3 Name = Rib_Root, index = 4 Name = Spar2, index = 5 Name = Rib_Root_Point, index = 6 Name = Wing, index = 7 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 365 Number of elements = 521 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 188 Elemental Quad4 = 333 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 366 Combined Number of elements = 522 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 188 Combined Elemental Quad4 = 333 Getting vortex lattice surface data VLM surface name - Skin_Top Done getting vortex lattice surface data Getting vortex lattice control surface data VLM control surface name - CntrlLE VLM control surface name - CntrlTE Done getting vortex lattice control surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 48 (Re-)Combining all aerodynamic surfaces into a 'Wing', 'Canard', and/or 'Fin' single surfaces ! Getting Aero Reference Parameters....... Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - Rib_Root No "material" specified for Property tuple Rib_Root, defaulting to an index of 1 Property name - Ribs No "material" specified for Property tuple Ribs, defaulting to an index of 1 Property name - Skin No "material" specified for Property tuple Skin, defaulting to an index of 1 Property name - Spar1 No "material" specified for Property tuple Spar1, defaulting to an index of 1 Property name - Spar2 No "material" specified for Property tuple Spar2, defaulting to an index of 1 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - ribConstraint No "constraintType" specified for Constraint tuple ribConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA supports....... Number of supports - 1 Support name - ribSupport Done getting FEA supports Getting FEA connections....... Number of connection tuples - 1 Connection name - Rib_Root No "groupName" specified for Connection tuple Rib_Root! Looking for automatic connections from the use of capsConnectLink for Rib_Root 42 automatic connections were made for capsConnect Rib_Root (node id 366) Done getting FEA connections Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Trim1 Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing connection cards - appending mesh file Writing Astros instruction file.... Writing aeros card Writing analysis cards Writing constraint cards--each subcase individually Writing support cards Writing material cards Writing property cards Writing aeroelastic cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL real 0m15.337s user 0m21.780s sys 0m3.108s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_Aeroelastic_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_AGARD445_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_AGARD445_PyTest.py test; + python -u astros_AGARD445_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Getting results natural frequencies..... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = constEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = yatesPlate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 36 Number of elements = 25 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 25 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Mahogany Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - yatesPlate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Writing analysis cards Writing constraint cards--all constraints for each subcase Writing material cards Writing property cards Reading Astros OUT file - extracting Eigen-Values! Number of Eigen-Values = 2 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Natural freq (Mode 1) = 5.78 (Hz) Natural freq (Mode 2) = 30.66 (Hz) real 0m1.248s user 0m0.943s sys 0m0.328s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_AGARD445_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_Composite_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_Composite_PyTest.py test; + python -u astros_Composite_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping Csys attributes ................ Number of unique Csys attributes = 1 Name = plate, index = 1 Getting FEA coordinate systems....... Number of coordinate systems - 1 Coordinate system name - plate Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plateTip, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 15 Number of elements = 8 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 8 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - cantilever No "constraintType" specified for Constraint tuple cantilever, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Writing analysis cards Writing constraint cards--all constraints for each subcase Writing material cards Writing property cards Writing coordinate system cards real 0m1.349s user 0m1.045s sys 0m0.413s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_Composite_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_CompositeWingFreq_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_CompositeWingFreq_PyTest.py test; + python -u astros_CompositeWingFreq_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Getting results for natural frequencies..... Mapping Csys attributes ................ Number of unique Csys attributes = 1 Name = wing, index = 1 Getting FEA coordinate systems....... Number of coordinate systems - 1 Coordinate system name - wing Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = wing, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = wing, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 5 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 6 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 7 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 429 Number of elements = 817 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 817 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Aluminum No "materialType" specified for Material tuple Aluminum, defaulting to "Isotropic" Material name - Graphite_epoxy Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - root No "constraintType" specified for Constraint tuple root, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Writing analysis cards Writing constraint cards--all constraints for each subcase Writing material cards Writing property cards Writing coordinate system cards Reading Astros OUT file - extracting Eigen-Values! Number of Eigen-Values = 10 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Loading Eigen-Value = 3 Loading Eigen-Value = 4 Loading Eigen-Value = 5 Loading Eigen-Value = 6 Loading Eigen-Value = 7 Loading Eigen-Value = 8 Loading Eigen-Value = 9 Loading Eigen-Value = 10 Natural freq (Mode 1) = 5.91949 (Hz) Natural freq (Mode 2) = 29.79990 (Hz) Natural freq (Mode 3) = 39.10550 (Hz) Natural freq (Mode 4) = 77.71580 (Hz) Natural freq (Mode 5) = 99.79550 (Hz) Natural freq (Mode 6) = 146.97500 (Hz) Natural freq (Mode 7) = 176.90300 (Hz) Natural freq (Mode 8) = 235.53300 (Hz) Natural freq (Mode 9) = 274.42600 (Hz) Natural freq (Mode 10) = 311.35900 (Hz) Reading Astros OUT file - extracting Eigen-Vectors! Number of Eigen-Vectors = 10 Number of Grid Points = 429 for each Eigen-Vector Loading Eigen-Vector = 1 Loading Eigen-Vector = 2 Loading Eigen-Vector = 3 Loading Eigen-Vector = 4 Loading Eigen-Vector = 5 Loading Eigen-Vector = 6 Loading Eigen-Vector = 7 Loading Eigen-Vector = 8 Loading Eigen-Vector = 9 Loading Eigen-Vector = 10 Reading Astros OUT file - extracting Eigen-Vectors! Number of Eigen-Vectors = 10 Number of Grid Points = 429 for each Eigen-Vector Loading Eigen-Vector = 1 Loading Eigen-Vector = 2 Loading Eigen-Vector = 3 Loading Eigen-Vector = 4 Loading Eigen-Vector = 5 Loading Eigen-Vector = 6 Loading Eigen-Vector = 7 Loading Eigen-Vector = 8 Loading Eigen-Vector = 9 Loading Eigen-Vector = 10 Reading Astros OUT file - extracting Eigen-Vectors! Number of Eigen-Vectors = 10 Number of Grid Points = 429 for each Eigen-Vector Loading Eigen-Vector = 1 Loading Eigen-Vector = 2 Loading Eigen-Vector = 3 Loading Eigen-Vector = 4 Loading Eigen-Vector = 5 Loading Eigen-Vector = 6 Loading Eigen-Vector = 7 Loading Eigen-Vector = 8 Loading Eigen-Vector = 9 Loading Eigen-Vector = 10 Reading Astros OUT file - extracting Eigen-Vectors! Number of Eigen-Vectors = 10 Number of Grid Points = 429 for each Eigen-Vector Loading Eigen-Vector = 1 Loading Eigen-Vector = 2 Loading Eigen-Vector = 3 Loading Eigen-Vector = 4 Loading Eigen-Vector = 5 Loading Eigen-Vector = 6 Loading Eigen-Vector = 7 Loading Eigen-Vector = 8 Loading Eigen-Vector = 9 Loading Eigen-Vector = 10 Reading Astros OUT file - extracting Eigen-Vectors! Number of Eigen-Vectors = 10 Number of Grid Points = 429 for each Eigen-Vector Loading Eigen-Vector = 1 Loading Eigen-Vector = 2 Loading Eigen-Vector = 3 Loading Eigen-Vector = 4 Loading Eigen-Vector = 5 Loading Eigen-Vector = 6 Loading Eigen-Vector = 7 Loading Eigen-Vector = 8 Loading Eigen-Vector = 9 Loading Eigen-Vector = 10 real 1m4.750s user 1m2.491s sys 0m1.736s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_CompositeWingFreq_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_Flutter_15degree.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_Flutter_15degree.py test; + python -u astros_Flutter_15degree.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Root_Point, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Root_Point, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = WingSurface, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = Root, index = 1 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Edge, index = 1 Name = Body, index = 2 Name = Root, index = 3 Name = Wing, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 96 Number of elements = 77 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 77 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 97 Combined Number of elements = 78 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 77 Getting vortex lattice surface data VLM surface name - WingSurface Done getting vortex lattice surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 96 (Re-)Combining all aerodynamic surfaces into a 'Wing', 'Canard', and/or 'Fin' single surfaces ! Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - aluminum No "materialType" specified for Material tuple aluminum, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Body Property name - Edge Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - PointConstraint No "constraintType" specified for Constraint tuple PointConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Getting FEA connections....... Number of connection tuples - 1 Connection name - Root No "groupName" specified for Connection tuple Root! Looking for automatic connections from the use of capsConnectLink for Root 8 automatic connections were made for capsConnect Root (node id 97) Done getting FEA connections Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Flutter Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing connection cards - appending mesh file Writing Astros instruction file.... Writing aero card Writing analysis cards Writing constraint cards--each subcase individually Writing material cards Writing property cards Writing unsteady aeroelastic cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL real 0m2.416s user 0m1.596s sys 0m0.721s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_Flutter_15degree.py passed (as expected) ================================================= ================================================= + echo 'astros_MultipleLoadCase_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_MultipleLoadCase_PyTest.py test; + python -u astros_MultipleLoadCase_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plate, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 16 Number of elements = 9 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 9 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 5 Load name - load_0 Load name - load_1 Load name - load_2 Load name - load_3 Load name - load_4 Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 5 Analysis name - load_0 Analysis name - load_1 Analysis name - load_2 Analysis name - load_3 Analysis name - load_4 Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case load_0, assuming all constraints are applied!!!! Warning: No constraints specified for case load_1, assuming all constraints are applied!!!! Warning: No constraints specified for case load_2, assuming all constraints are applied!!!! Warning: No constraints specified for case load_3, assuming all constraints are applied!!!! Warning: No constraints specified for case load_4, assuming all constraints are applied!!!! Writing analysis cards Writing load ADD cards Writing constraint cards--all constraints for each subcase Writing load ADD cards Writing constraint cards--all constraints for each subcase Writing load ADD cards Writing constraint cards--all constraints for each subcase Writing load ADD cards Writing constraint cards--all constraints for each subcase Writing load ADD cards Writing constraint cards--all constraints for each subcase Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL real 0m2.117s user 0m1.412s sys 0m0.550s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_MultipleLoadCase_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_PyTest.py test; + python -u astros_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Getting results for natural frequencies..... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Ribs_and_Spars, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 293 Number of elements = 217 Number of triangle elements = 0 Number of quadrilateral elements = 217 ---------------------------- Total number of nodes = 293 Total number of elements = 217 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Constraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Ribs_and_Spars, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 293 Number of elements = 217 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 217 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - Ribs_and_Spars Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - ribConstraint No "constraintType" specified for Constraint tuple ribConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Writing analysis cards Writing constraint cards--all constraints for each subcase Writing material cards Writing property cards Reading Astros OUT file - extracting Eigen-Values! Number of Eigen-Values = 10 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Loading Eigen-Value = 3 Loading Eigen-Value = 4 Loading Eigen-Value = 5 Loading Eigen-Value = 6 Loading Eigen-Value = 7 Loading Eigen-Value = 8 Loading Eigen-Value = 9 Loading Eigen-Value = 10 Natural freq (Mode 1) = 0.02335 (Hz) Natural freq (Mode 2) = 0.02335 (Hz) Natural freq (Mode 3) = 0.11619 (Hz) Natural freq (Mode 4) = 0.11619 (Hz) Natural freq (Mode 5) = 0.14468 (Hz) Natural freq (Mode 6) = 0.14468 (Hz) Natural freq (Mode 7) = 0.23352 (Hz) Natural freq (Mode 8) = 0.23352 (Hz) Natural freq (Mode 9) = 0.30497 (Hz) Natural freq (Mode 10) = 0.30497 (Hz) real 0m21.692s user 0m23.423s sys 0m3.000s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_SingleLoadCase_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_SingleLoadCase_PyTest.py test; + python -u astros_SingleLoadCase_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plate, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 12 Number of elements = 6 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 6 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedPressure Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL real 0m1.315s user 0m1.009s sys 0m0.406s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_SingleLoadCase_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_ThreeBarFreq_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_ThreeBarFreq_PyTest.py test; + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt + python -u astros_ThreeBarFreq_PyTest.py -outLevel=0 Getting results for natural frequencies..... WARNING:: WireBody is non-manifold Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = boundary, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 capsIgnore attribute found for edge - 3!! capsIgnore attribute found. Removing unneeded nodes and elements from mesh! Removing unused nodes... Removed 0 (out of 4) unused nodes! Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 4 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 3 Elemental Tria3 = 0 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - bar1 Property name - bar2 Property name - bar3 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - BoundaryCondition No "constraintType" specified for Constraint tuple BoundaryCondition, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Writing analysis cards Writing constraint cards--all constraints for each subcase Writing material cards Writing property cards Reading Astros OUT file - extracting Eigen-Values! Number of Eigen-Values = 2 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Natural freq (Mode 1) = 86.13400 (Hz) Natural freq (Mode 2) = 168.53300 (Hz) real 0m1.350s user 0m1.029s sys 0m0.384s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_ThreeBarFreq_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_ThreeBarLinkDesign_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_ThreeBarLinkDesign_PyTest.py test; + python -u astros_ThreeBarLinkDesign_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt WARNING:: WireBody is non-manifold Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = boundary, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 capsIgnore attribute found for edge - 3!! capsIgnore attribute found. Removing unneeded nodes and elements from mesh! Removing unused nodes... Removed 0 (out of 4) unused nodes! Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 4 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 3 Elemental Tria3 = 0 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - bar1 Property name - bar2 Property name - bar3 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - BoundaryCondition No "constraintType" specified for Constraint tuple BoundaryCondition, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedForce Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Getting FEA design variables....... Number of design variables - 3 Design_Variable name - Bar1A Design_Variable name - Bar2A Design_Variable name - Bar3A Design_Variable_Relation name - Bar1A Design_Variable_Relation name - Bar2A Design_Variable_Relation name - Bar3A Number of design variable relations - 3 Done getting FEA design variables Getting FEA design constraints....... Number of design constraints - 3 Design_Constraint name - stress1 Design_Constraint name - stress2 Design_Constraint name - stress3 Done getting FEA design constraints Getting FEA analyses....... Number of analyses - 1 Analysis name - SingleLoadCase Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing design constraint cards Writing load cards Writing material cards Writing property cards Writing design variable cards Running Astros...... Done running Astros! real 0m1.515s user 0m1.137s sys 0m0.380s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_ThreeBarLinkDesign_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_ThreeBarMultiLoad_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_ThreeBarMultiLoad_PyTest.py test; + python -u astros_ThreeBarMultiLoad_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt WARNING:: WireBody is non-manifold Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = boundary, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 capsIgnore attribute found for edge - 3!! capsIgnore attribute found. Removing unneeded nodes and elements from mesh! Removing unused nodes... Removed 0 (out of 4) unused nodes! Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 4 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 3 Elemental Tria3 = 0 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - bar1 Property name - bar2 Property name - bar3 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 2 Constraint name - conOne No "constraintType" specified for Constraint tuple conOne, defaulting to "ZeroDisplacement" Constraint name - conTwo No "constraintType" specified for Constraint tuple conTwo, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - loadOne Load name - loadTwo Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 2 Analysis name - analysisOne Analysis name - analysisTwo Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards real 0m1.226s user 0m0.974s sys 0m0.358s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_ThreeBarMultiLoad_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_ThreeBar_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_ThreeBar_PyTest.py test; + python -u astros_ThreeBar_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt WARNING:: WireBody is non-manifold Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = boundary, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 capsIgnore attribute found for edge - 3!! capsIgnore attribute found. Removing unneeded nodes and elements from mesh! Removing unused nodes... Removed 0 (out of 4) unused nodes! Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 4 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 3 Elemental Tria3 = 0 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - bar1 Property name - bar2 Property name - bar3 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - BoundaryCondition No "constraintType" specified for Constraint tuple BoundaryCondition, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedForce Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - SingleLoadCase Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards real 0m1.225s user 0m0.962s sys 0m0.370s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_ThreeBar_PyTest.py passed (as expected) ================================================= ================================================= + echo 'astros_Trim_15degree.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt astros_Trim_15degree.py test; + python -u astros_Trim_15degree.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Root_Point, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Root_Point, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = WingSurface, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = Root, index = 1 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Edge, index = 1 Name = Body, index = 2 Name = Root, index = 3 Name = Wing, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 96 Number of elements = 77 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 77 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 97 Combined Number of elements = 78 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 77 Getting vortex lattice surface data VLM surface name - WingSurface Done getting vortex lattice surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 96 (Re-)Combining all aerodynamic surfaces into a 'Wing', 'Canard', and/or 'Fin' single surfaces ! Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - aluminum No "materialType" specified for Material tuple aluminum, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - Body Property name - Edge Property name - Root Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - PointConstraint No "constraintType" specified for Constraint tuple PointConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA supports....... Number of supports - 1 Support name - PointSupport Done getting FEA supports Getting FEA connections....... Number of connection tuples - 1 Connection name - Root No "groupName" specified for Connection tuple Root! Looking for automatic connections from the use of capsConnectLink for Root 8 automatic connections were made for capsConnect Root (node id 97) Done getting FEA connections Getting FEA loads....... Number of loads - 2 Load name - GravityLoad No "groupName" specified for Load tuple GravityLoad, going to use load name Load name - PointLoad Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Trim Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing connection cards - appending mesh file Writing Astros instruction file.... Writing aeros card Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing support cards Writing material cards Writing property cards Writing aeroelastic cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL real 0m1.697s user 0m1.275s sys 0m0.487s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case astros_Trim_15degree.py passed (as expected) ================================================= ================================================= + echo 'nastran_AGARD445_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_AGARD445_PyTest.py test; + python -u nastran_AGARD445_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = yatesPlate, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 49 Number of elements = 36 Number of triangle elements = 0 Number of quadrilateral elements = 36 ---------------------------- Total number of nodes = 49 Total number of elements = 36 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = constEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = yatesPlate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 49 Number of elements = 36 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 36 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Mahogany Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - yatesPlate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Nastran grid and connectivity file (in free field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Warning: No loads specified for case EigenAnalysis!!!! Writing mass increment cards Writing analysis cards, 0 Writing combined constraint cards Writing constraint cards Writing material cards Writing property cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! Getting results natural frequencies..... Reading Nastran FO6 file - extracting Eigen-Values! Number of Eigen-Values = 132 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Loading Eigen-Value = 3 Loading Eigen-Value = 4 Loading Eigen-Value = 5 Loading Eigen-Value = 6 Loading Eigen-Value = 7 Loading Eigen-Value = 8 Loading Eigen-Value = 9 Loading Eigen-Value = 10 Loading Eigen-Value = 11 Loading Eigen-Value = 12 Loading Eigen-Value = 13 Loading Eigen-Value = 14 Loading Eigen-Value = 15 Loading Eigen-Value = 16 Loading Eigen-Value = 17 Loading Eigen-Value = 18 Loading Eigen-Value = 19 Loading Eigen-Value = 20 Loading Eigen-Value = 21 Loading Eigen-Value = 22 Loading Eigen-Value = 23 Loading Eigen-Value = 24 Loading Eigen-Value = 25 Loading Eigen-Value = 26 Loading Eigen-Value = 27 Loading Eigen-Value = 28 Loading Eigen-Value = 29 Loading Eigen-Value = 30 Loading Eigen-Value = 31 Loading Eigen-Value = 32 Loading Eigen-Value = 33 Loading Eigen-Value = 34 Loading Eigen-Value = 35 Loading Eigen-Value = 36 Loading Eigen-Value = 37 Loading Eigen-Value = 38 Loading Eigen-Value = 39 Loading Eigen-Value = 40 Loading Eigen-Value = 41 Loading Eigen-Value = 42 Loading Eigen-Value = 43 Loading Eigen-Value = 44 Loading Eigen-Value = 45 Loading Eigen-Value = 46 Loading Eigen-Value = 47 Loading Eigen-Value = 48 Loading Eigen-Value = 49 Loading Eigen-Value = 50 Loading Eigen-Value = 51 Loading Eigen-Value = 52 Loading Eigen-Value = 53 Loading Eigen-Value = 54 Loading Eigen-Value = 55 Loading Eigen-Value = 56 Loading Eigen-Value = 57 Loading Eigen-Value = 58 Loading Eigen-Value = 59 Loading Eigen-Value = 60 Loading Eigen-Value = 61 Loading Eigen-Value = 62 Loading Eigen-Value = 63 Loading Eigen-Value = 64 Loading Eigen-Value = 65 Loading Eigen-Value = 66 Loading Eigen-Value = 67 Loading Eigen-Value = 68 Loading Eigen-Value = 69 Loading Eigen-Value = 70 Loading Eigen-Value = 71 Loading Eigen-Value = 72 Loading Eigen-Value = 73 Loading Eigen-Value = 74 Loading Eigen-Value = 75 Loading Eigen-Value = 76 Loading Eigen-Value = 77 Loading Eigen-Value = 78 Loading Eigen-Value = 79 Loading Eigen-Value = 80 Loading Eigen-Value = 81 Loading Eigen-Value = 82 Loading Eigen-Value = 83 Loading Eigen-Value = 84 Loading Eigen-Value = 85 Loading Eigen-Value = 86 Loading Eigen-Value = 87 Loading Eigen-Value = 88 Loading Eigen-Value = 89 Loading Eigen-Value = 90 Loading Eigen-Value = 91 Loading Eigen-Value = 92 Loading Eigen-Value = 93 Loading Eigen-Value = 94 Loading Eigen-Value = 95 Loading Eigen-Value = 96 Loading Eigen-Value = 97 Loading Eigen-Value = 98 Loading Eigen-Value = 99 Loading Eigen-Value = 100 Loading Eigen-Value = 101 Loading Eigen-Value = 102 Loading Eigen-Value = 103 Loading Eigen-Value = 104 Loading Eigen-Value = 105 Loading Eigen-Value = 106 Loading Eigen-Value = 107 Loading Eigen-Value = 108 Loading Eigen-Value = 109 Loading Eigen-Value = 110 Loading Eigen-Value = 111 Loading Eigen-Value = 112 Loading Eigen-Value = 113 Loading Eigen-Value = 114 Loading Eigen-Value = 115 Loading Eigen-Value = 116 Loading Eigen-Value = 117 Loading Eigen-Value = 118 Loading Eigen-Value = 119 Loading Eigen-Value = 120 Loading Eigen-Value = 121 Loading Eigen-Value = 122 Loading Eigen-Value = 123 Loading Eigen-Value = 124 Loading Eigen-Value = 125 Loading Eigen-Value = 126 Loading Eigen-Value = 127 Loading Eigen-Value = 128 Loading Eigen-Value = 129 Loading Eigen-Value = 130 Loading Eigen-Value = 131 Loading Eigen-Value = 132 Natural freq (Mode 0) = 9.44 (Hz) Natural freq (Mode 1) = 35.99 (Hz) Natural freq (Mode 2) = 50.58 (Hz) Natural freq (Mode 3) = 93.48 (Hz) Natural freq (Mode 4) = 122.58 (Hz) Natural freq (Mode 5) = 142.96 (Hz) Natural freq (Mode 6) = 153.81 (Hz) Natural freq (Mode 7) = 201.18 (Hz) Natural freq (Mode 8) = 203.69 (Hz) Natural freq (Mode 9) = 218.54 (Hz) Natural freq (Mode 10) = 244.49 (Hz) Natural freq (Mode 11) = 267.52 (Hz) Natural freq (Mode 12) = 282.33 (Hz) Natural freq (Mode 13) = 284.46 (Hz) Natural freq (Mode 14) = 311.84 (Hz) Natural freq (Mode 15) = 328.87 (Hz) Natural freq (Mode 16) = 334.68 (Hz) Natural freq (Mode 17) = 346.25 (Hz) Natural freq (Mode 18) = 362.24 (Hz) Natural freq (Mode 19) = 368.68 (Hz) Natural freq (Mode 20) = 377.76 (Hz) Natural freq (Mode 21) = 393.48 (Hz) Natural freq (Mode 22) = 403.01 (Hz) Natural freq (Mode 23) = 415.98 (Hz) Natural freq (Mode 24) = 430.66 (Hz) Natural freq (Mode 25) = 456.25 (Hz) Natural freq (Mode 26) = 460.70 (Hz) Natural freq (Mode 27) = 478.12 (Hz) Natural freq (Mode 28) = 500.39 (Hz) Natural freq (Mode 29) = 510.45 (Hz) Natural freq (Mode 30) = 514.48 (Hz) Natural freq (Mode 31) = 519.72 (Hz) Natural freq (Mode 32) = 531.28 (Hz) Natural freq (Mode 33) = 553.76 (Hz) Natural freq (Mode 34) = 566.65 (Hz) Natural freq (Mode 35) = 591.27 (Hz) Natural freq (Mode 36) = 611.71 (Hz) Natural freq (Mode 37) = 612.08 (Hz) Natural freq (Mode 38) = 624.35 (Hz) Natural freq (Mode 39) = 650.56 (Hz) Natural freq (Mode 40) = 670.08 (Hz) Natural freq (Mode 41) = 721.11 (Hz) Natural freq (Mode 42) = 732.49 (Hz) Natural freq (Mode 43) = 751.28 (Hz) Natural freq (Mode 44) = 814.54 (Hz) Natural freq (Mode 45) = 883.96 (Hz) Natural freq (Mode 46) = 951.75 (Hz) Natural freq (Mode 47) = 975.90 (Hz) Natural freq (Mode 48) = 1290.98 (Hz) Natural freq (Mode 49) = 1356.05 (Hz) Natural freq (Mode 50) = 1506.01 (Hz) Natural freq (Mode 51) = 1619.60 (Hz) Natural freq (Mode 52) = 1631.13 (Hz) Natural freq (Mode 53) = 1745.44 (Hz) Natural freq (Mode 54) = 1904.47 (Hz) Natural freq (Mode 55) = 2010.78 (Hz) Natural freq (Mode 56) = 2031.59 (Hz) Natural freq (Mode 57) = 2108.70 (Hz) Natural freq (Mode 58) = 2215.97 (Hz) Natural freq (Mode 59) = 2306.66 (Hz) Natural freq (Mode 60) = 2320.15 (Hz) Natural freq (Mode 61) = 2390.78 (Hz) Natural freq (Mode 62) = 2494.64 (Hz) Natural freq (Mode 63) = 2560.50 (Hz) Natural freq (Mode 64) = 2584.60 (Hz) Natural freq (Mode 65) = 2587.28 (Hz) Natural freq (Mode 66) = 2659.52 (Hz) Natural freq (Mode 67) = 2737.71 (Hz) Natural freq (Mode 68) = 2789.18 (Hz) Natural freq (Mode 69) = 2840.95 (Hz) Natural freq (Mode 70) = 2888.34 (Hz) Natural freq (Mode 71) = 2967.46 (Hz) Natural freq (Mode 72) = 3051.49 (Hz) Natural freq (Mode 73) = 3112.98 (Hz) Natural freq (Mode 74) = 3139.85 (Hz) Natural freq (Mode 75) = 3247.88 (Hz) Natural freq (Mode 76) = 3303.45 (Hz) Natural freq (Mode 77) = 3344.57 (Hz) Natural freq (Mode 78) = 3466.41 (Hz) Natural freq (Mode 79) = 3489.29 (Hz) Natural freq (Mode 80) = 3562.75 (Hz) Natural freq (Mode 81) = 3651.56 (Hz) Natural freq (Mode 82) = 3712.84 (Hz) Natural freq (Mode 83) = 3761.27 (Hz) Natural freq (Mode 84) = 3806.30 (Hz) Natural freq (Mode 85) = 3902.83 (Hz) Natural freq (Mode 86) = 3961.00 (Hz) Natural freq (Mode 87) = 4028.45 (Hz) Natural freq (Mode 88) = 4110.02 (Hz) Natural freq (Mode 89) = 4191.05 (Hz) Natural freq (Mode 90) = 4202.44 (Hz) Natural freq (Mode 91) = 4299.35 (Hz) Natural freq (Mode 92) = 4376.59 (Hz) Natural freq (Mode 93) = 4425.85 (Hz) Natural freq (Mode 94) = 4501.49 (Hz) Natural freq (Mode 95) = 4518.77 (Hz) Natural freq (Mode 96) = 4586.52 (Hz) Natural freq (Mode 97) = 4621.28 (Hz) Natural freq (Mode 98) = 4678.52 (Hz) Natural freq (Mode 99) = 4733.41 (Hz) Natural freq (Mode 100) = 4788.76 (Hz) Natural freq (Mode 101) = 4816.52 (Hz) Natural freq (Mode 102) = 4942.47 (Hz) Natural freq (Mode 103) = 4997.55 (Hz) Natural freq (Mode 104) = 5045.56 (Hz) Natural freq (Mode 105) = 5120.59 (Hz) Natural freq (Mode 106) = 5155.17 (Hz) Natural freq (Mode 107) = 5325.08 (Hz) Natural freq (Mode 108) = 5474.54 (Hz) Natural freq (Mode 109) = 5512.48 (Hz) Natural freq (Mode 110) = 5525.67 (Hz) Natural freq (Mode 111) = 5576.25 (Hz) Natural freq (Mode 112) = 5647.01 (Hz) Natural freq (Mode 113) = 5841.96 (Hz) Natural freq (Mode 114) = 6096.57 (Hz) Natural freq (Mode 115) = 6188.63 (Hz) Natural freq (Mode 116) = 6328.76 (Hz) Natural freq (Mode 117) = 6428.94 (Hz) Natural freq (Mode 118) = 6468.91 (Hz) Natural freq (Mode 119) = 6958.88 (Hz) Natural freq (Mode 120) = 7050.41 (Hz) Natural freq (Mode 121) = 7389.46 (Hz) Natural freq (Mode 122) = 7464.28 (Hz) Natural freq (Mode 123) = 7559.48 (Hz) Natural freq (Mode 124) = 8076.62 (Hz) Natural freq (Mode 125) = 8344.67 (Hz) Natural freq (Mode 126) = 8685.13 (Hz) Natural freq (Mode 127) = 9093.83 (Hz) Natural freq (Mode 128) = 9351.46 (Hz) Natural freq (Mode 129) = 10123.65 (Hz) Natural freq (Mode 130) = 10828.55 (Hz) Natural freq (Mode 131) = 11674.11 (Hz) real 0m1.603s user 0m0.979s sys 0m0.621s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_AGARD445_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_Aeroelastic_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_Aeroelastic_PyTest.py test; + python -u nastran_Aeroelastic_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = Ribs, index = 1 Name = Skin, index = 2 Name = Spar1, index = 3 Name = Rib_Root, index = 4 Name = Spar2, index = 5 Name = Rib_Root_Point, index = 6 Name = Wing, index = 7 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = LeadingEdge, index = 1 Name = TrailingEdge, index = 2 Getting surface mesh for body 1 (of 4) Getting surface mesh for body 2 (of 4) Getting surface mesh for body 3 (of 4) Getting surface mesh for body 4 (of 4) Body 1 (of 4) Number of nodes = 1377 Number of elements = 1514 Number of triangle elements = 0 Number of quadrilateral elements = 1514 Body 2 (of 4) Number of nodes = 1 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 Body 3 (of 4) Number of nodes = 17 Number of elements = 10 Number of triangle elements = 0 Number of quadrilateral elements = 10 Body 4 (of 4) Number of nodes = 17 Number of elements = 10 Number of triangle elements = 0 Number of quadrilateral elements = 10 ---------------------------- Total number of nodes = 1412 Total number of elements = 1534 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root_Point, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = Skin_Top, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = Rib_Root, index = 1 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 1 Name = Rib_Root_Point, index = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 7 Name = Ribs, index = 1 Name = Skin, index = 2 Name = Spar1, index = 3 Name = Rib_Root, index = 4 Name = Spar2, index = 5 Name = Rib_Root_Point, index = 6 Name = Wing, index = 7 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 1377 Number of elements = 1514 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 1514 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 17 Number of elements = 10 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 10 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 17 Number of elements = 10 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 10 Combining multiple FEA meshes! Combined Number of nodal coordinates = 1412 Combined Number of elements = 1535 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 1534 Getting vortex lattice surface data VLM surface name - Skin_Top Done getting vortex lattice surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 300 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - Rib_Root No "material" specified for Property tuple Rib_Root, defaulting to an index of 1 Property name - Ribs No "material" specified for Property tuple Ribs, defaulting to an index of 1 Property name - Skin No "material" specified for Property tuple Skin, defaulting to an index of 1 Property name - Spar1 No "material" specified for Property tuple Spar1, defaulting to an index of 1 Property name - Spar2 No "material" specified for Property tuple Spar2, defaulting to an index of 1 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - ribConstraint No "constraintType" specified for Constraint tuple ribConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA supports....... Number of supports - 1 Support name - ribSupport Done getting FEA supports Getting FEA connections....... Number of connection tuples - 1 Connection name - Rib_Root No "groupName" specified for Connection tuple Rib_Root! Looking for automatic connections from the use of capsConnectLink for Rib_Root 93 automatic connections were made for capsConnect Rib_Root (node id 1378) Done getting FEA connections Load tuple is NULL - No loads applied Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Trim1 Done getting FEA analyses Writing Nastran grid and connectivity file (in free field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing connection cards - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No loads specified for case Trim1!!!! Writing mass increment cards Writing aeros card Writing aestat cards Writing analysis cards, 0 Writing constraint ADD cards Writing constraint cards Writing support cards Writing material cards Writing property cards Writing aeroelastic cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m10.554s user 0m16.793s sys 0m2.332s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_Aeroelastic_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_CompositeWingDesign_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_CompositeWingDesign_PyTest.py test; + python -u nastran_CompositeWingDesign_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 290 Number of elements = 229 Number of triangle elements = 0 Number of quadrilateral elements = 229 ---------------------------- Total number of nodes = 290 Total number of elements = 229 Mapping Csys attributes ................ Number of unique Csys attributes = 1 Name = wing, index = 1 Getting FEA coordinate systems....... Number of coordinate systems - 1 Coordinate system name - wing Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = wing, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = wing, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 5 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 6 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 7 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 290 Number of elements = 229 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 229 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Aluminum No "materialType" specified for Material tuple Aluminum, defaulting to "Isotropic" Material name - Graphite_epoxy Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - BoundaryCondition No "constraintType" specified for Constraint tuple BoundaryCondition, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedPressure Done getting FEA loads Getting FEA design variables....... Number of design variables - 8 Design_Variable name - L1 Design_Variable name - L2 Design_Variable name - L3 Design_Variable name - L4 Design_Variable name - L5 Design_Variable name - L6 Design_Variable name - L7 Design_Variable name - L8 Design_Variable_Relation name - L1R Design_Variable_Relation name - L2R Design_Variable_Relation name - L3R Design_Variable_Relation name - L4R Design_Variable_Relation name - L5R Design_Variable_Relation name - L6R Design_Variable_Relation name - L7R Design_Variable_Relation name - L8R Number of design variable relations - 8 Done getting FEA design variables Getting FEA design constraints....... Number of design constraints - 8 Design_Constraint name - stress1 Design_Constraint name - stress2 Design_Constraint name - stress3 Design_Constraint name - stress4 Design_Constraint name - stress5 Design_Constraint name - stress6 Design_Constraint name - stress7 Design_Constraint name - stress8 Done getting FEA design constraints Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - StaticAnalysis Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Writing mass increment cards Writing analysis cards, 0 Writing load ADD cards Writing constraint ADD cards Writing design constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Writing coordinate system cards Writing design variable cards Writing design variable relation cards Writing design constraints and responses cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m2.467s user 0m1.655s sys 0m0.665s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_CompositeWingDesign_PyTest.py passed (as expected) ================================================= ================================================= + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt + echo 'nastran_CompositeWingFreq_PyTest.py test;' nastran_CompositeWingFreq_PyTest.py test; + python -u nastran_CompositeWingFreq_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 290 Number of elements = 229 Number of triangle elements = 0 Number of quadrilateral elements = 229 ---------------------------- Total number of nodes = 290 Total number of elements = 229 Mapping Csys attributes ................ Number of unique Csys attributes = 1 Name = wing, index = 1 Getting FEA coordinate systems....... Number of coordinate systems - 1 Coordinate system name - wing Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = wing, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = wing, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 5 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 6 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 7 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 290 Number of elements = 229 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 229 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Aluminum No "materialType" specified for Material tuple Aluminum, defaulting to "Isotropic" Material name - Graphite_epoxy Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - root No "constraintType" specified for Constraint tuple root, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Warning: No loads specified for case EigenAnalysis!!!! Writing mass increment cards Writing analysis cards, 0 Writing combined constraint cards Writing constraint cards Writing material cards Writing property cards Writing coordinate system cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! Getting results for natural frequencies..... Reading Nastran FO6 file - extracting Eigen-Values! Number of Eigen-Values = 1779 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Loading Eigen-Value = 3 Loading Eigen-Value = 4 Loading Eigen-Value = 5 Loading Eigen-Value = 6 Loading Eigen-Value = 7 Loading Eigen-Value = 8 Loading Eigen-Value = 9 Loading Eigen-Value = 10 Loading Eigen-Value = 11 Loading Eigen-Value = 12 Loading Eigen-Value = 13 Loading Eigen-Value = 14 Loading Eigen-Value = 15 Loading Eigen-Value = 16 Loading Eigen-Value = 17 Loading Eigen-Value = 18 Loading Eigen-Value = 19 Loading Eigen-Value = 20 Loading Eigen-Value = 21 Loading Eigen-Value = 22 Loading Eigen-Value = 23 Loading Eigen-Value = 24 Loading Eigen-Value = 25 Loading Eigen-Value = 26 Loading Eigen-Value = 27 Loading Eigen-Value = 28 Loading Eigen-Value = 29 Loading Eigen-Value = 30 Loading Eigen-Value = 31 Loading Eigen-Value = 32 Loading Eigen-Value = 33 Loading Eigen-Value = 34 Loading Eigen-Value = 35 Loading Eigen-Value = 36 Loading Eigen-Value = 37 Loading Eigen-Value = 38 Loading Eigen-Value = 39 Loading Eigen-Value = 40 Loading Eigen-Value = 41 Loading Eigen-Value = 42 Loading Eigen-Value = 43 Loading Eigen-Value = 44 Loading Eigen-Value = 45 Loading Eigen-Value = 46 Loading Eigen-Value = 47 Loading Eigen-Value = 48 Loading Eigen-Value = 49 Loading Eigen-Value = 50 Loading Eigen-Value = 51 Loading Eigen-Value = 52 Loading Eigen-Value = 53 Loading Eigen-Value = 54 Loading Eigen-Value = 55 Loading Eigen-Value = 56 Loading Eigen-Value = 57 Loading Eigen-Value = 58 Loading Eigen-Value = 59 Loading Eigen-Value = 60 Loading Eigen-Value = 61 Loading Eigen-Value = 62 Loading Eigen-Value = 63 Loading Eigen-Value = 64 Loading Eigen-Value = 65 Loading Eigen-Value = 66 Loading Eigen-Value = 67 Loading Eigen-Value = 68 Loading Eigen-Value = 69 Loading Eigen-Value = 70 Loading Eigen-Value = 71 Loading Eigen-Value = 72 Loading Eigen-Value = 73 Loading Eigen-Value = 74 Loading Eigen-Value = 75 Loading Eigen-Value = 76 Loading Eigen-Value = 77 Loading Eigen-Value = 78 Loading Eigen-Value = 79 Loading Eigen-Value = 80 Loading Eigen-Value = 81 Loading Eigen-Value = 82 Loading Eigen-Value = 83 Loading Eigen-Value = 84 Loading Eigen-Value = 85 Loading Eigen-Value = 86 Loading Eigen-Value = 87 Loading Eigen-Value = 88 Loading Eigen-Value = 89 Loading Eigen-Value = 90 Loading Eigen-Value = 91 Loading Eigen-Value = 92 Loading Eigen-Value = 93 Loading Eigen-Value = 94 Loading Eigen-Value = 95 Loading Eigen-Value = 96 Loading Eigen-Value = 97 Loading Eigen-Value = 98 Loading Eigen-Value = 99 Loading Eigen-Value = 100 Loading Eigen-Value = 101 Loading Eigen-Value = 102 Loading Eigen-Value = 103 Loading Eigen-Value = 104 Loading Eigen-Value = 105 Loading Eigen-Value = 106 Loading Eigen-Value = 107 Loading Eigen-Value = 108 Loading Eigen-Value = 109 Loading Eigen-Value = 110 Loading Eigen-Value = 111 Loading Eigen-Value = 112 Loading Eigen-Value = 113 Loading Eigen-Value = 114 Loading Eigen-Value = 115 Loading Eigen-Value = 116 Loading Eigen-Value = 117 Loading Eigen-Value = 118 Loading Eigen-Value = 119 Loading Eigen-Value = 120 Loading Eigen-Value = 121 Loading Eigen-Value = 122 Loading Eigen-Value = 123 Loading Eigen-Value = 124 Loading Eigen-Value = 125 Loading Eigen-Value = 126 Loading Eigen-Value = 127 Loading Eigen-Value = 128 Loading Eigen-Value = 129 Loading Eigen-Value = 130 Loading Eigen-Value = 131 Loading Eigen-Value = 132 Loading Eigen-Value = 133 Loading Eigen-Value = 134 Loading Eigen-Value = 135 Loading Eigen-Value = 136 Loading Eigen-Value = 137 Loading Eigen-Value = 138 Loading Eigen-Value = 139 Loading Eigen-Value = 140 Loading Eigen-Value = 141 Loading Eigen-Value = 142 Loading Eigen-Value = 143 Loading Eigen-Value = 144 Loading Eigen-Value = 145 Loading Eigen-Value = 146 Loading Eigen-Value = 147 Loading Eigen-Value = 148 Loading Eigen-Value = 149 Loading Eigen-Value = 150 Loading Eigen-Value = 151 Loading Eigen-Value = 152 Loading Eigen-Value = 153 Loading Eigen-Value = 154 Loading Eigen-Value = 155 Loading Eigen-Value = 156 Loading Eigen-Value = 157 Loading Eigen-Value = 158 Loading Eigen-Value = 159 Loading Eigen-Value = 160 Loading Eigen-Value = 161 Loading Eigen-Value = 162 Loading Eigen-Value = 163 Loading Eigen-Value = 164 Loading Eigen-Value = 165 Loading Eigen-Value = 166 Loading Eigen-Value = 167 Loading Eigen-Value = 168 Loading Eigen-Value = 169 Loading Eigen-Value = 170 Loading Eigen-Value = 171 Loading Eigen-Value = 172 Loading Eigen-Value = 173 Loading Eigen-Value = 174 Loading Eigen-Value = 175 Loading Eigen-Value = 176 Loading Eigen-Value = 177 Loading Eigen-Value = 178 Loading Eigen-Value = 179 Loading Eigen-Value = 180 Loading Eigen-Value = 181 Loading Eigen-Value = 182 Loading Eigen-Value = 183 Loading Eigen-Value = 184 Loading Eigen-Value = 185 Loading Eigen-Value = 186 Loading Eigen-Value = 187 Loading Eigen-Value = 188 Loading Eigen-Value = 189 Loading Eigen-Value = 190 Loading Eigen-Value = 191 Loading Eigen-Value = 192 Loading Eigen-Value = 193 Loading Eigen-Value = 194 Loading Eigen-Value = 195 Loading Eigen-Value = 196 Loading Eigen-Value = 197 Loading Eigen-Value = 198 Loading Eigen-Value = 199 Loading Eigen-Value = 200 Loading Eigen-Value = 201 Loading Eigen-Value = 202 Loading Eigen-Value = 203 Loading Eigen-Value = 204 Loading Eigen-Value = 205 Loading Eigen-Value = 206 Loading Eigen-Value = 207 Loading Eigen-Value = 208 Loading Eigen-Value = 209 Loading Eigen-Value = 210 Loading Eigen-Value = 211 Loading Eigen-Value = 212 Loading Eigen-Value = 213 Loading Eigen-Value = 214 Loading Eigen-Value = 215 Loading Eigen-Value = 216 Loading Eigen-Value = 217 Loading Eigen-Value = 218 Loading Eigen-Value = 219 Loading Eigen-Value = 220 Loading Eigen-Value = 221 Loading Eigen-Value = 222 Loading Eigen-Value = 223 Loading Eigen-Value = 224 Loading Eigen-Value = 225 Loading Eigen-Value = 226 Loading Eigen-Value = 227 Loading Eigen-Value = 228 Loading Eigen-Value = 229 Loading Eigen-Value = 230 Loading Eigen-Value = 231 Loading Eigen-Value = 232 Loading Eigen-Value = 233 Loading Eigen-Value = 234 Loading Eigen-Value = 235 Loading Eigen-Value = 236 Loading Eigen-Value = 237 Loading Eigen-Value = 238 Loading Eigen-Value = 239 Loading Eigen-Value = 240 Loading Eigen-Value = 241 Loading Eigen-Value = 242 Loading Eigen-Value = 243 Loading Eigen-Value = 244 Loading Eigen-Value = 245 Loading Eigen-Value = 246 Loading Eigen-Value = 247 Loading Eigen-Value = 248 Loading Eigen-Value = 249 Loading Eigen-Value = 250 Loading Eigen-Value = 251 Loading Eigen-Value = 252 Loading Eigen-Value = 253 Loading Eigen-Value = 254 Loading Eigen-Value = 255 Loading Eigen-Value = 256 Loading Eigen-Value = 257 Loading Eigen-Value = 258 Loading Eigen-Value = 259 Loading Eigen-Value = 260 Loading Eigen-Value = 261 Loading Eigen-Value = 262 Loading Eigen-Value = 263 Loading Eigen-Value = 264 Loading Eigen-Value = 265 Loading Eigen-Value = 266 Loading Eigen-Value = 267 Loading Eigen-Value = 268 Loading Eigen-Value = 269 Loading Eigen-Value = 270 Loading Eigen-Value = 271 Loading Eigen-Value = 272 Loading Eigen-Value = 273 Loading Eigen-Value = 274 Loading Eigen-Value = 275 Loading Eigen-Value = 276 Loading Eigen-Value = 277 Loading Eigen-Value = 278 Loading Eigen-Value = 279 Loading Eigen-Value = 280 Loading Eigen-Value = 281 Loading Eigen-Value = 282 Loading Eigen-Value = 283 Loading Eigen-Value = 284 Loading Eigen-Value = 285 Loading Eigen-Value = 286 Loading Eigen-Value = 287 Loading Eigen-Value = 288 Loading Eigen-Value = 289 Loading Eigen-Value = 290 Loading Eigen-Value = 291 Loading Eigen-Value = 292 Loading Eigen-Value = 293 Loading Eigen-Value = 294 Loading Eigen-Value = 295 Loading Eigen-Value = 296 Loading Eigen-Value = 297 Loading Eigen-Value = 298 Loading Eigen-Value = 299 Loading Eigen-Value = 300 Loading Eigen-Value = 301 Loading Eigen-Value = 302 Loading Eigen-Value = 303 Loading Eigen-Value = 304 Loading Eigen-Value = 305 Loading Eigen-Value = 306 Loading Eigen-Value = 307 Loading Eigen-Value = 308 Loading Eigen-Value = 309 Loading Eigen-Value = 310 Loading Eigen-Value = 311 Loading Eigen-Value = 312 Loading Eigen-Value = 313 Loading Eigen-Value = 314 Loading Eigen-Value = 315 Loading Eigen-Value = 316 Loading Eigen-Value = 317 Loading Eigen-Value = 318 Loading Eigen-Value = 319 Loading Eigen-Value = 320 Loading Eigen-Value = 321 Loading Eigen-Value = 322 Loading Eigen-Value = 323 Loading Eigen-Value = 324 Loading Eigen-Value = 325 Loading Eigen-Value = 326 Loading Eigen-Value = 327 Loading Eigen-Value = 328 Loading Eigen-Value = 329 Loading Eigen-Value = 330 Loading Eigen-Value = 331 Loading Eigen-Value = 332 Loading Eigen-Value = 333 Loading Eigen-Value = 334 Loading Eigen-Value = 335 Loading Eigen-Value = 336 Loading Eigen-Value = 337 Loading Eigen-Value = 338 Loading Eigen-Value = 339 Loading Eigen-Value = 340 Loading Eigen-Value = 341 Loading Eigen-Value = 342 Loading Eigen-Value = 343 Loading Eigen-Value = 344 Loading Eigen-Value = 345 Loading Eigen-Value = 346 Loading Eigen-Value = 347 Loading Eigen-Value = 348 Loading Eigen-Value = 349 Loading Eigen-Value = 350 Loading Eigen-Value = 351 Loading Eigen-Value = 352 Loading Eigen-Value = 353 Loading Eigen-Value = 354 Loading Eigen-Value = 355 Loading Eigen-Value = 356 Loading Eigen-Value = 357 Loading Eigen-Value = 358 Loading Eigen-Value = 359 Loading Eigen-Value = 360 Loading Eigen-Value = 361 Loading Eigen-Value = 362 Loading Eigen-Value = 363 Loading Eigen-Value = 364 Loading Eigen-Value = 365 Loading Eigen-Value = 366 Loading Eigen-Value = 367 Loading Eigen-Value = 368 Loading Eigen-Value = 369 Loading Eigen-Value = 370 Loading Eigen-Value = 371 Loading Eigen-Value = 372 Loading Eigen-Value = 373 Loading Eigen-Value = 374 Loading Eigen-Value = 375 Loading Eigen-Value = 376 Loading Eigen-Value = 377 Loading Eigen-Value = 378 Loading Eigen-Value = 379 Loading Eigen-Value = 380 Loading Eigen-Value = 381 Loading Eigen-Value = 382 Loading Eigen-Value = 383 Loading Eigen-Value = 384 Loading Eigen-Value = 385 Loading Eigen-Value = 386 Loading Eigen-Value = 387 Loading Eigen-Value = 388 Loading Eigen-Value = 389 Loading Eigen-Value = 390 Loading Eigen-Value = 391 Loading Eigen-Value = 392 Loading Eigen-Value = 393 Loading Eigen-Value = 394 Loading Eigen-Value = 395 Loading Eigen-Value = 396 Loading Eigen-Value = 397 Loading Eigen-Value = 398 Loading Eigen-Value = 399 Loading Eigen-Value = 400 Loading Eigen-Value = 401 Loading Eigen-Value = 402 Loading Eigen-Value = 403 Loading Eigen-Value = 404 Loading Eigen-Value = 405 Loading Eigen-Value = 406 Loading Eigen-Value = 407 Loading Eigen-Value = 408 Loading Eigen-Value = 409 Loading Eigen-Value = 410 Loading Eigen-Value = 411 Loading Eigen-Value = 412 Loading Eigen-Value = 413 Loading Eigen-Value = 414 Loading Eigen-Value = 415 Loading Eigen-Value = 416 Loading Eigen-Value = 417 Loading Eigen-Value = 418 Loading Eigen-Value = 419 Loading Eigen-Value = 420 Loading Eigen-Value = 421 Loading Eigen-Value = 422 Loading Eigen-Value = 423 Loading Eigen-Value = 424 Loading Eigen-Value = 425 Loading Eigen-Value = 426 Loading Eigen-Value = 427 Loading Eigen-Value = 428 Loading Eigen-Value = 429 Loading Eigen-Value = 430 Loading Eigen-Value = 431 Loading Eigen-Value = 432 Loading Eigen-Value = 433 Loading Eigen-Value = 434 Loading Eigen-Value = 435 Loading Eigen-Value = 436 Loading Eigen-Value = 437 Loading Eigen-Value = 438 Loading Eigen-Value = 439 Loading Eigen-Value = 440 Loading Eigen-Value = 441 Loading Eigen-Value = 442 Loading Eigen-Value = 443 Loading Eigen-Value = 444 Loading Eigen-Value = 445 Loading Eigen-Value = 446 Loading Eigen-Value = 447 Loading Eigen-Value = 448 Loading Eigen-Value = 449 Loading Eigen-Value = 450 Loading Eigen-Value = 451 Loading Eigen-Value = 452 Loading Eigen-Value = 453 Loading Eigen-Value = 454 Loading Eigen-Value = 455 Loading Eigen-Value = 456 Loading Eigen-Value = 457 Loading Eigen-Value = 458 Loading Eigen-Value = 459 Loading Eigen-Value = 460 Loading Eigen-Value = 461 Loading Eigen-Value = 462 Loading Eigen-Value = 463 Loading Eigen-Value = 464 Loading Eigen-Value = 465 Loading Eigen-Value = 466 Loading Eigen-Value = 467 Loading Eigen-Value = 468 Loading Eigen-Value = 469 Loading Eigen-Value = 470 Loading Eigen-Value = 471 Loading Eigen-Value = 472 Loading Eigen-Value = 473 Loading Eigen-Value = 474 Loading Eigen-Value = 475 Loading Eigen-Value = 476 Loading Eigen-Value = 477 Loading Eigen-Value = 478 Loading Eigen-Value = 479 Loading Eigen-Value = 480 Loading Eigen-Value = 481 Loading Eigen-Value = 482 Loading Eigen-Value = 483 Loading Eigen-Value = 484 Loading Eigen-Value = 485 Loading Eigen-Value = 486 Loading Eigen-Value = 487 Loading Eigen-Value = 488 Loading Eigen-Value = 489 Loading Eigen-Value = 490 Loading Eigen-Value = 491 Loading Eigen-Value = 492 Loading Eigen-Value = 493 Loading Eigen-Value = 494 Loading Eigen-Value = 495 Loading Eigen-Value = 496 Loading Eigen-Value = 497 Loading Eigen-Value = 498 Loading Eigen-Value = 499 Loading Eigen-Value = 500 Loading Eigen-Value = 501 Loading Eigen-Value = 502 Loading Eigen-Value = 503 Loading Eigen-Value = 504 Loading Eigen-Value = 505 Loading Eigen-Value = 506 Loading Eigen-Value = 507 Loading Eigen-Value = 508 Loading Eigen-Value = 509 Loading Eigen-Value = 510 Loading Eigen-Value = 511 Loading Eigen-Value = 512 Loading Eigen-Value = 513 Loading Eigen-Value = 514 Loading Eigen-Value = 515 Loading Eigen-Value = 516 Loading Eigen-Value = 517 Loading Eigen-Value = 518 Loading Eigen-Value = 519 Loading Eigen-Value = 520 Loading Eigen-Value = 521 Loading Eigen-Value = 522 Loading Eigen-Value = 523 Loading Eigen-Value = 524 Loading Eigen-Value = 525 Loading Eigen-Value = 526 Loading Eigen-Value = 527 Loading Eigen-Value = 528 Loading Eigen-Value = 529 Loading Eigen-Value = 530 Loading Eigen-Value = 531 Loading Eigen-Value = 532 Loading Eigen-Value = 533 Loading Eigen-Value = 534 Loading Eigen-Value = 535 Loading Eigen-Value = 536 Loading Eigen-Value = 537 Loading Eigen-Value = 538 Loading Eigen-Value = 539 Loading Eigen-Value = 540 Loading Eigen-Value = 541 Loading Eigen-Value = 542 Loading Eigen-Value = 543 Loading Eigen-Value = 544 Loading Eigen-Value = 545 Loading Eigen-Value = 546 Loading Eigen-Value = 547 Loading Eigen-Value = 548 Loading Eigen-Value = 549 Loading Eigen-Value = 550 Loading Eigen-Value = 551 Loading Eigen-Value = 552 Loading Eigen-Value = 553 Loading Eigen-Value = 554 Loading Eigen-Value = 555 Loading Eigen-Value = 556 Loading Eigen-Value = 557 Loading Eigen-Value = 558 Loading Eigen-Value = 559 Loading Eigen-Value = 560 Loading Eigen-Value = 561 Loading Eigen-Value = 562 Loading Eigen-Value = 563 Loading Eigen-Value = 564 Loading Eigen-Value = 565 Loading Eigen-Value = 566 Loading Eigen-Value = 567 Loading Eigen-Value = 568 Loading Eigen-Value = 569 Loading Eigen-Value = 570 Loading Eigen-Value = 571 Loading Eigen-Value = 572 Loading Eigen-Value = 573 Loading Eigen-Value = 574 Loading Eigen-Value = 575 Loading Eigen-Value = 576 Loading Eigen-Value = 577 Loading Eigen-Value = 578 Loading Eigen-Value = 579 Loading Eigen-Value = 580 Loading Eigen-Value = 581 Loading Eigen-Value = 582 Loading Eigen-Value = 583 Loading Eigen-Value = 584 Loading Eigen-Value = 585 Loading Eigen-Value = 586 Loading Eigen-Value = 587 Loading Eigen-Value = 588 Loading Eigen-Value = 589 Loading Eigen-Value = 590 Loading Eigen-Value = 591 Loading Eigen-Value = 592 Loading Eigen-Value = 593 Loading Eigen-Value = 594 Loading Eigen-Value = 595 Loading Eigen-Value = 596 Loading Eigen-Value = 597 Loading Eigen-Value = 598 Loading Eigen-Value = 599 Loading Eigen-Value = 600 Loading Eigen-Value = 601 Loading Eigen-Value = 602 Loading Eigen-Value = 603 Loading Eigen-Value = 604 Loading Eigen-Value = 605 Loading Eigen-Value = 606 Loading Eigen-Value = 607 Loading Eigen-Value = 608 Loading Eigen-Value = 609 Loading Eigen-Value = 610 Loading Eigen-Value = 611 Loading Eigen-Value = 612 Loading Eigen-Value = 613 Loading Eigen-Value = 614 Loading Eigen-Value = 615 Loading Eigen-Value = 616 Loading Eigen-Value = 617 Loading Eigen-Value = 618 Loading Eigen-Value = 619 Loading Eigen-Value = 620 Loading Eigen-Value = 621 Loading Eigen-Value = 622 Loading Eigen-Value = 623 Loading Eigen-Value = 624 Loading Eigen-Value = 625 Loading Eigen-Value = 626 Loading Eigen-Value = 627 Loading Eigen-Value = 628 Loading Eigen-Value = 629 Loading Eigen-Value = 630 Loading Eigen-Value = 631 Loading Eigen-Value = 632 Loading Eigen-Value = 633 Loading Eigen-Value = 634 Loading Eigen-Value = 635 Loading Eigen-Value = 636 Loading Eigen-Value = 637 Loading Eigen-Value = 638 Loading Eigen-Value = 639 Loading Eigen-Value = 640 Loading Eigen-Value = 641 Loading Eigen-Value = 642 Loading Eigen-Value = 643 Loading Eigen-Value = 644 Loading Eigen-Value = 645 Loading Eigen-Value = 646 Loading Eigen-Value = 647 Loading Eigen-Value = 648 Loading Eigen-Value = 649 Loading Eigen-Value = 650 Loading Eigen-Value = 651 Loading Eigen-Value = 652 Loading Eigen-Value = 653 Loading Eigen-Value = 654 Loading Eigen-Value = 655 Loading Eigen-Value = 656 Loading Eigen-Value = 657 Loading Eigen-Value = 658 Loading Eigen-Value = 659 Loading Eigen-Value = 660 Loading Eigen-Value = 661 Loading Eigen-Value = 662 Loading Eigen-Value = 663 Loading Eigen-Value = 664 Loading Eigen-Value = 665 Loading Eigen-Value = 666 Loading Eigen-Value = 667 Loading Eigen-Value = 668 Loading Eigen-Value = 669 Loading Eigen-Value = 670 Loading Eigen-Value = 671 Loading Eigen-Value = 672 Loading Eigen-Value = 673 Loading Eigen-Value = 674 Loading Eigen-Value = 675 Loading Eigen-Value = 676 Loading Eigen-Value = 677 Loading Eigen-Value = 678 Loading Eigen-Value = 679 Loading Eigen-Value = 680 Loading Eigen-Value = 681 Loading Eigen-Value = 682 Loading Eigen-Value = 683 Loading Eigen-Value = 684 Loading Eigen-Value = 685 Loading Eigen-Value = 686 Loading Eigen-Value = 687 Loading Eigen-Value = 688 Loading Eigen-Value = 689 Loading Eigen-Value = 690 Loading Eigen-Value = 691 Loading Eigen-Value = 692 Loading Eigen-Value = 693 Loading Eigen-Value = 694 Loading Eigen-Value = 695 Loading Eigen-Value = 696 Loading Eigen-Value = 697 Loading Eigen-Value = 698 Loading Eigen-Value = 699 Loading Eigen-Value = 700 Loading Eigen-Value = 701 Loading Eigen-Value = 702 Loading Eigen-Value = 703 Loading Eigen-Value = 704 Loading Eigen-Value = 705 Loading Eigen-Value = 706 Loading Eigen-Value = 707 Loading Eigen-Value = 708 Loading Eigen-Value = 709 Loading Eigen-Value = 710 Loading Eigen-Value = 711 Loading Eigen-Value = 712 Loading Eigen-Value = 713 Loading Eigen-Value = 714 Loading Eigen-Value = 715 Loading Eigen-Value = 716 Loading Eigen-Value = 717 Loading Eigen-Value = 718 Loading Eigen-Value = 719 Loading Eigen-Value = 720 Loading Eigen-Value = 721 Loading Eigen-Value = 722 Loading Eigen-Value = 723 Loading Eigen-Value = 724 Loading Eigen-Value = 725 Loading Eigen-Value = 726 Loading Eigen-Value = 727 Loading Eigen-Value = 728 Loading Eigen-Value = 729 Loading Eigen-Value = 730 Loading Eigen-Value = 731 Loading Eigen-Value = 732 Loading Eigen-Value = 733 Loading Eigen-Value = 734 Loading Eigen-Value = 735 Loading Eigen-Value = 736 Loading Eigen-Value = 737 Loading Eigen-Value = 738 Loading Eigen-Value = 739 Loading Eigen-Value = 740 Loading Eigen-Value = 741 Loading Eigen-Value = 742 Loading Eigen-Value = 743 Loading Eigen-Value = 744 Loading Eigen-Value = 745 Loading Eigen-Value = 746 Loading Eigen-Value = 747 Loading Eigen-Value = 748 Loading Eigen-Value = 749 Loading Eigen-Value = 750 Loading Eigen-Value = 751 Loading Eigen-Value = 752 Loading Eigen-Value = 753 Loading Eigen-Value = 754 Loading Eigen-Value = 755 Loading Eigen-Value = 756 Loading Eigen-Value = 757 Loading Eigen-Value = 758 Loading Eigen-Value = 759 Loading Eigen-Value = 760 Loading Eigen-Value = 761 Loading Eigen-Value = 762 Loading Eigen-Value = 763 Loading Eigen-Value = 764 Loading Eigen-Value = 765 Loading Eigen-Value = 766 Loading Eigen-Value = 767 Loading Eigen-Value = 768 Loading Eigen-Value = 769 Loading Eigen-Value = 770 Loading Eigen-Value = 771 Loading Eigen-Value = 772 Loading Eigen-Value = 773 Loading Eigen-Value = 774 Loading Eigen-Value = 775 Loading Eigen-Value = 776 Loading Eigen-Value = 777 Loading Eigen-Value = 778 Loading Eigen-Value = 779 Loading Eigen-Value = 780 Loading Eigen-Value = 781 Loading Eigen-Value = 782 Loading Eigen-Value = 783 Loading Eigen-Value = 784 Loading Eigen-Value = 785 Loading Eigen-Value = 786 Loading Eigen-Value = 787 Loading Eigen-Value = 788 Loading Eigen-Value = 789 Loading Eigen-Value = 790 Loading Eigen-Value = 791 Loading Eigen-Value = 792 Loading Eigen-Value = 793 Loading Eigen-Value = 794 Loading Eigen-Value = 795 Loading Eigen-Value = 796 Loading Eigen-Value = 797 Loading Eigen-Value = 798 Loading Eigen-Value = 799 Loading Eigen-Value = 800 Loading Eigen-Value = 801 Loading Eigen-Value = 802 Loading Eigen-Value = 803 Loading Eigen-Value = 804 Loading Eigen-Value = 805 Loading Eigen-Value = 806 Loading Eigen-Value = 807 Loading Eigen-Value = 808 Loading Eigen-Value = 809 Loading Eigen-Value = 810 Loading Eigen-Value = 811 Loading Eigen-Value = 812 Loading Eigen-Value = 813 Loading Eigen-Value = 814 Loading Eigen-Value = 815 Loading Eigen-Value = 816 Loading Eigen-Value = 817 Loading Eigen-Value = 818 Loading Eigen-Value = 819 Loading Eigen-Value = 820 Loading Eigen-Value = 821 Loading Eigen-Value = 822 Loading Eigen-Value = 823 Loading Eigen-Value = 824 Loading Eigen-Value = 825 Loading Eigen-Value = 826 Loading Eigen-Value = 827 Loading Eigen-Value = 828 Loading Eigen-Value = 829 Loading Eigen-Value = 830 Loading Eigen-Value = 831 Loading Eigen-Value = 832 Loading Eigen-Value = 833 Loading Eigen-Value = 834 Loading Eigen-Value = 835 Loading Eigen-Value = 836 Loading Eigen-Value = 837 Loading Eigen-Value = 838 Loading Eigen-Value = 839 Loading Eigen-Value = 840 Loading Eigen-Value = 841 Loading Eigen-Value = 842 Loading Eigen-Value = 843 Loading Eigen-Value = 844 Loading Eigen-Value = 845 Loading Eigen-Value = 846 Loading Eigen-Value = 847 Loading Eigen-Value = 848 Loading Eigen-Value = 849 Loading Eigen-Value = 850 Loading Eigen-Value = 851 Loading Eigen-Value = 852 Loading Eigen-Value = 853 Loading Eigen-Value = 854 Loading Eigen-Value = 855 Loading Eigen-Value = 856 Loading Eigen-Value = 857 Loading Eigen-Value = 858 Loading Eigen-Value = 859 Loading Eigen-Value = 860 Loading Eigen-Value = 861 Loading Eigen-Value = 862 Loading Eigen-Value = 863 Loading Eigen-Value = 864 Loading Eigen-Value = 865 Loading Eigen-Value = 866 Loading Eigen-Value = 867 Loading Eigen-Value = 868 Loading Eigen-Value = 869 Loading Eigen-Value = 870 Loading Eigen-Value = 871 Loading Eigen-Value = 872 Loading Eigen-Value = 873 Loading Eigen-Value = 874 Loading Eigen-Value = 875 Loading Eigen-Value = 876 Loading Eigen-Value = 877 Loading Eigen-Value = 878 Loading Eigen-Value = 879 Loading Eigen-Value = 880 Loading Eigen-Value = 881 Loading Eigen-Value = 882 Loading Eigen-Value = 883 Loading Eigen-Value = 884 Loading Eigen-Value = 885 Loading Eigen-Value = 886 Loading Eigen-Value = 887 Loading Eigen-Value = 888 Loading Eigen-Value = 889 Loading Eigen-Value = 890 Loading Eigen-Value = 891 Loading Eigen-Value = 892 Loading Eigen-Value = 893 Loading Eigen-Value = 894 Loading Eigen-Value = 895 Loading Eigen-Value = 896 Loading Eigen-Value = 897 Loading Eigen-Value = 898 Loading Eigen-Value = 899 Loading Eigen-Value = 900 Loading Eigen-Value = 901 Loading Eigen-Value = 902 Loading Eigen-Value = 903 Loading Eigen-Value = 904 Loading Eigen-Value = 905 Loading Eigen-Value = 906 Loading Eigen-Value = 907 Loading Eigen-Value = 908 Loading Eigen-Value = 909 Loading Eigen-Value = 910 Loading Eigen-Value = 911 Loading Eigen-Value = 912 Loading Eigen-Value = 913 Loading Eigen-Value = 914 Loading Eigen-Value = 915 Loading Eigen-Value = 916 Loading Eigen-Value = 917 Loading Eigen-Value = 918 Loading Eigen-Value = 919 Loading Eigen-Value = 920 Loading Eigen-Value = 921 Loading Eigen-Value = 922 Loading Eigen-Value = 923 Loading Eigen-Value = 924 Loading Eigen-Value = 925 Loading Eigen-Value = 926 Loading Eigen-Value = 927 Loading Eigen-Value = 928 Loading Eigen-Value = 929 Loading Eigen-Value = 930 Loading Eigen-Value = 931 Loading Eigen-Value = 932 Loading Eigen-Value = 933 Loading Eigen-Value = 934 Loading Eigen-Value = 935 Loading Eigen-Value = 936 Loading Eigen-Value = 937 Loading Eigen-Value = 938 Loading Eigen-Value = 939 Loading Eigen-Value = 940 Loading Eigen-Value = 941 Loading Eigen-Value = 942 Loading Eigen-Value = 943 Loading Eigen-Value = 944 Loading Eigen-Value = 945 Loading Eigen-Value = 946 Loading Eigen-Value = 947 Loading Eigen-Value = 948 Loading Eigen-Value = 949 Loading Eigen-Value = 950 Loading Eigen-Value = 951 Loading Eigen-Value = 952 Loading Eigen-Value = 953 Loading Eigen-Value = 954 Loading Eigen-Value = 955 Loading Eigen-Value = 956 Loading Eigen-Value = 957 Loading Eigen-Value = 958 Loading Eigen-Value = 959 Loading Eigen-Value = 960 Loading Eigen-Value = 961 Loading Eigen-Value = 962 Loading Eigen-Value = 963 Loading Eigen-Value = 964 Loading Eigen-Value = 965 Loading Eigen-Value = 966 Loading Eigen-Value = 967 Loading Eigen-Value = 968 Loading Eigen-Value = 969 Loading Eigen-Value = 970 Loading Eigen-Value = 971 Loading Eigen-Value = 972 Loading Eigen-Value = 973 Loading Eigen-Value = 974 Loading Eigen-Value = 975 Loading Eigen-Value = 976 Loading Eigen-Value = 977 Loading Eigen-Value = 978 Loading Eigen-Value = 979 Loading Eigen-Value = 980 Loading Eigen-Value = 981 Loading Eigen-Value = 982 Loading Eigen-Value = 983 Loading Eigen-Value = 984 Loading Eigen-Value = 985 Loading Eigen-Value = 986 Loading Eigen-Value = 987 Loading Eigen-Value = 988 Loading Eigen-Value = 989 Loading Eigen-Value = 990 Loading Eigen-Value = 991 Loading Eigen-Value = 992 Loading Eigen-Value = 993 Loading Eigen-Value = 994 Loading Eigen-Value = 995 Loading Eigen-Value = 996 Loading Eigen-Value = 997 Loading Eigen-Value = 998 Loading Eigen-Value = 999 Loading Eigen-Value = 1000 Loading Eigen-Value = 1001 Loading Eigen-Value = 1002 Loading Eigen-Value = 1003 Loading Eigen-Value = 1004 Loading Eigen-Value = 1005 Loading Eigen-Value = 1006 Loading Eigen-Value = 1007 Loading Eigen-Value = 1008 Loading Eigen-Value = 1009 Loading Eigen-Value = 1010 Loading Eigen-Value = 1011 Loading Eigen-Value = 1012 Loading Eigen-Value = 1013 Loading Eigen-Value = 1014 Loading Eigen-Value = 1015 Loading Eigen-Value = 1016 Loading Eigen-Value = 1017 Loading Eigen-Value = 1018 Loading Eigen-Value = 1019 Loading Eigen-Value = 1020 Loading Eigen-Value = 1021 Loading Eigen-Value = 1022 Loading Eigen-Value = 1023 Loading Eigen-Value = 1024 Loading Eigen-Value = 1025 Loading Eigen-Value = 1026 Loading Eigen-Value = 1027 Loading Eigen-Value = 1028 Loading Eigen-Value = 1029 Loading Eigen-Value = 1030 Loading Eigen-Value = 1031 Loading Eigen-Value = 1032 Loading Eigen-Value = 1033 Loading Eigen-Value = 1034 Loading Eigen-Value = 1035 Loading Eigen-Value = 1036 Loading Eigen-Value = 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1111 Loading Eigen-Value = 1112 Loading Eigen-Value = 1113 Loading Eigen-Value = 1114 Loading Eigen-Value = 1115 Loading Eigen-Value = 1116 Loading Eigen-Value = 1117 Loading Eigen-Value = 1118 Loading Eigen-Value = 1119 Loading Eigen-Value = 1120 Loading Eigen-Value = 1121 Loading Eigen-Value = 1122 Loading Eigen-Value = 1123 Loading Eigen-Value = 1124 Loading Eigen-Value = 1125 Loading Eigen-Value = 1126 Loading Eigen-Value = 1127 Loading Eigen-Value = 1128 Loading Eigen-Value = 1129 Loading Eigen-Value = 1130 Loading Eigen-Value = 1131 Loading Eigen-Value = 1132 Loading Eigen-Value = 1133 Loading Eigen-Value = 1134 Loading Eigen-Value = 1135 Loading Eigen-Value = 1136 Loading Eigen-Value = 1137 Loading Eigen-Value = 1138 Loading Eigen-Value = 1139 Loading Eigen-Value = 1140 Loading Eigen-Value = 1141 Loading Eigen-Value = 1142 Loading Eigen-Value = 1143 Loading Eigen-Value = 1144 Loading Eigen-Value = 1145 Loading Eigen-Value = 1146 Loading Eigen-Value = 1147 Loading Eigen-Value = 1148 Loading Eigen-Value = 1149 Loading Eigen-Value = 1150 Loading Eigen-Value = 1151 Loading Eigen-Value = 1152 Loading Eigen-Value = 1153 Loading Eigen-Value = 1154 Loading Eigen-Value = 1155 Loading Eigen-Value = 1156 Loading Eigen-Value = 1157 Loading Eigen-Value = 1158 Loading Eigen-Value = 1159 Loading Eigen-Value = 1160 Loading Eigen-Value = 1161 Loading Eigen-Value = 1162 Loading Eigen-Value = 1163 Loading Eigen-Value = 1164 Loading Eigen-Value = 1165 Loading Eigen-Value = 1166 Loading Eigen-Value = 1167 Loading Eigen-Value = 1168 Loading Eigen-Value = 1169 Loading Eigen-Value = 1170 Loading Eigen-Value = 1171 Loading Eigen-Value = 1172 Loading Eigen-Value = 1173 Loading Eigen-Value = 1174 Loading Eigen-Value = 1175 Loading Eigen-Value = 1176 Loading Eigen-Value = 1177 Loading Eigen-Value = 1178 Loading Eigen-Value = 1179 Loading Eigen-Value = 1180 Loading Eigen-Value = 1181 Loading Eigen-Value = 1182 Loading Eigen-Value = 1183 Loading Eigen-Value = 1184 Loading Eigen-Value = 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1333 Loading Eigen-Value = 1334 Loading Eigen-Value = 1335 Loading Eigen-Value = 1336 Loading Eigen-Value = 1337 Loading Eigen-Value = 1338 Loading Eigen-Value = 1339 Loading Eigen-Value = 1340 Loading Eigen-Value = 1341 Loading Eigen-Value = 1342 Loading Eigen-Value = 1343 Loading Eigen-Value = 1344 Loading Eigen-Value = 1345 Loading Eigen-Value = 1346 Loading Eigen-Value = 1347 Loading Eigen-Value = 1348 Loading Eigen-Value = 1349 Loading Eigen-Value = 1350 Loading Eigen-Value = 1351 Loading Eigen-Value = 1352 Loading Eigen-Value = 1353 Loading Eigen-Value = 1354 Loading Eigen-Value = 1355 Loading Eigen-Value = 1356 Loading Eigen-Value = 1357 Loading Eigen-Value = 1358 Loading Eigen-Value = 1359 Loading Eigen-Value = 1360 Loading Eigen-Value = 1361 Loading Eigen-Value = 1362 Loading Eigen-Value = 1363 Loading Eigen-Value = 1364 Loading Eigen-Value = 1365 Loading Eigen-Value = 1366 Loading Eigen-Value = 1367 Loading Eigen-Value = 1368 Loading Eigen-Value = 1369 Loading Eigen-Value = 1370 Loading Eigen-Value = 1371 Loading Eigen-Value = 1372 Loading Eigen-Value = 1373 Loading Eigen-Value = 1374 Loading Eigen-Value = 1375 Loading Eigen-Value = 1376 Loading Eigen-Value = 1377 Loading Eigen-Value = 1378 Loading Eigen-Value = 1379 Loading Eigen-Value = 1380 Loading Eigen-Value = 1381 Loading Eigen-Value = 1382 Loading Eigen-Value = 1383 Loading Eigen-Value = 1384 Loading Eigen-Value = 1385 Loading Eigen-Value = 1386 Loading Eigen-Value = 1387 Loading Eigen-Value = 1388 Loading Eigen-Value = 1389 Loading Eigen-Value = 1390 Loading Eigen-Value = 1391 Loading Eigen-Value = 1392 Loading Eigen-Value = 1393 Loading Eigen-Value = 1394 Loading Eigen-Value = 1395 Loading Eigen-Value = 1396 Loading Eigen-Value = 1397 Loading Eigen-Value = 1398 Loading Eigen-Value = 1399 Loading Eigen-Value = 1400 Loading Eigen-Value = 1401 Loading Eigen-Value = 1402 Loading Eigen-Value = 1403 Loading Eigen-Value = 1404 Loading Eigen-Value = 1405 Loading Eigen-Value = 1406 Loading Eigen-Value = 1407 Loading Eigen-Value = 1408 Loading Eigen-Value = 1409 Loading Eigen-Value = 1410 Loading Eigen-Value = 1411 Loading Eigen-Value = 1412 Loading Eigen-Value = 1413 Loading Eigen-Value = 1414 Loading Eigen-Value = 1415 Loading Eigen-Value = 1416 Loading Eigen-Value = 1417 Loading Eigen-Value = 1418 Loading Eigen-Value = 1419 Loading Eigen-Value = 1420 Loading Eigen-Value = 1421 Loading Eigen-Value = 1422 Loading Eigen-Value = 1423 Loading Eigen-Value = 1424 Loading Eigen-Value = 1425 Loading Eigen-Value = 1426 Loading Eigen-Value = 1427 Loading Eigen-Value = 1428 Loading Eigen-Value = 1429 Loading Eigen-Value = 1430 Loading Eigen-Value = 1431 Loading Eigen-Value = 1432 Loading Eigen-Value = 1433 Loading Eigen-Value = 1434 Loading Eigen-Value = 1435 Loading Eigen-Value = 1436 Loading Eigen-Value = 1437 Loading Eigen-Value = 1438 Loading Eigen-Value = 1439 Loading Eigen-Value = 1440 Loading Eigen-Value = 1441 Loading Eigen-Value = 1442 Loading Eigen-Value = 1443 Loading Eigen-Value = 1444 Loading Eigen-Value = 1445 Loading Eigen-Value = 1446 Loading Eigen-Value = 1447 Loading Eigen-Value = 1448 Loading Eigen-Value = 1449 Loading Eigen-Value = 1450 Loading Eigen-Value = 1451 Loading Eigen-Value = 1452 Loading Eigen-Value = 1453 Loading Eigen-Value = 1454 Loading Eigen-Value = 1455 Loading Eigen-Value = 1456 Loading Eigen-Value = 1457 Loading Eigen-Value = 1458 Loading Eigen-Value = 1459 Loading Eigen-Value = 1460 Loading Eigen-Value = 1461 Loading Eigen-Value = 1462 Loading Eigen-Value = 1463 Loading Eigen-Value = 1464 Loading Eigen-Value = 1465 Loading Eigen-Value = 1466 Loading Eigen-Value = 1467 Loading Eigen-Value = 1468 Loading Eigen-Value = 1469 Loading Eigen-Value = 1470 Loading Eigen-Value = 1471 Loading Eigen-Value = 1472 Loading Eigen-Value = 1473 Loading Eigen-Value = 1474 Loading Eigen-Value = 1475 Loading Eigen-Value = 1476 Loading Eigen-Value = 1477 Loading Eigen-Value = 1478 Loading Eigen-Value = 1479 Loading Eigen-Value = 1480 Loading Eigen-Value = 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1518 Loading Eigen-Value = 1519 Loading Eigen-Value = 1520 Loading Eigen-Value = 1521 Loading Eigen-Value = 1522 Loading Eigen-Value = 1523 Loading Eigen-Value = 1524 Loading Eigen-Value = 1525 Loading Eigen-Value = 1526 Loading Eigen-Value = 1527 Loading Eigen-Value = 1528 Loading Eigen-Value = 1529 Loading Eigen-Value = 1530 Loading Eigen-Value = 1531 Loading Eigen-Value = 1532 Loading Eigen-Value = 1533 Loading Eigen-Value = 1534 Loading Eigen-Value = 1535 Loading Eigen-Value = 1536 Loading Eigen-Value = 1537 Loading Eigen-Value = 1538 Loading Eigen-Value = 1539 Loading Eigen-Value = 1540 Loading Eigen-Value = 1541 Loading Eigen-Value = 1542 Loading Eigen-Value = 1543 Loading Eigen-Value = 1544 Loading Eigen-Value = 1545 Loading Eigen-Value = 1546 Loading Eigen-Value = 1547 Loading Eigen-Value = 1548 Loading Eigen-Value = 1549 Loading Eigen-Value = 1550 Loading Eigen-Value = 1551 Loading Eigen-Value = 1552 Loading Eigen-Value = 1553 Loading Eigen-Value = 1554 Loading Eigen-Value = 1555 Loading Eigen-Value = 1556 Loading Eigen-Value = 1557 Loading Eigen-Value = 1558 Loading Eigen-Value = 1559 Loading Eigen-Value = 1560 Loading Eigen-Value = 1561 Loading Eigen-Value = 1562 Loading Eigen-Value = 1563 Loading Eigen-Value = 1564 Loading Eigen-Value = 1565 Loading Eigen-Value = 1566 Loading Eigen-Value = 1567 Loading Eigen-Value = 1568 Loading Eigen-Value = 1569 Loading Eigen-Value = 1570 Loading Eigen-Value = 1571 Loading Eigen-Value = 1572 Loading Eigen-Value = 1573 Loading Eigen-Value = 1574 Loading Eigen-Value = 1575 Loading Eigen-Value = 1576 Loading Eigen-Value = 1577 Loading Eigen-Value = 1578 Loading Eigen-Value = 1579 Loading Eigen-Value = 1580 Loading Eigen-Value = 1581 Loading Eigen-Value = 1582 Loading Eigen-Value = 1583 Loading Eigen-Value = 1584 Loading Eigen-Value = 1585 Loading Eigen-Value = 1586 Loading Eigen-Value = 1587 Loading Eigen-Value = 1588 Loading Eigen-Value = 1589 Loading Eigen-Value = 1590 Loading Eigen-Value = 1591 Loading Eigen-Value = 1592 Loading Eigen-Value = 1593 Loading Eigen-Value = 1594 Loading Eigen-Value = 1595 Loading Eigen-Value = 1596 Loading Eigen-Value = 1597 Loading Eigen-Value = 1598 Loading Eigen-Value = 1599 Loading Eigen-Value = 1600 Loading Eigen-Value = 1601 Loading Eigen-Value = 1602 Loading Eigen-Value = 1603 Loading Eigen-Value = 1604 Loading Eigen-Value = 1605 Loading Eigen-Value = 1606 Loading Eigen-Value = 1607 Loading Eigen-Value = 1608 Loading Eigen-Value = 1609 Loading Eigen-Value = 1610 Loading Eigen-Value = 1611 Loading Eigen-Value = 1612 Loading Eigen-Value = 1613 Loading Eigen-Value = 1614 Loading Eigen-Value = 1615 Loading Eigen-Value = 1616 Loading Eigen-Value = 1617 Loading Eigen-Value = 1618 Loading Eigen-Value = 1619 Loading Eigen-Value = 1620 Loading Eigen-Value = 1621 Loading Eigen-Value = 1622 Loading Eigen-Value = 1623 Loading Eigen-Value = 1624 Loading Eigen-Value = 1625 Loading Eigen-Value = 1626 Loading Eigen-Value = 1627 Loading Eigen-Value = 1628 Loading Eigen-Value = 1629 Loading Eigen-Value = 1630 Loading Eigen-Value = 1631 Loading Eigen-Value = 1632 Loading Eigen-Value = 1633 Loading Eigen-Value = 1634 Loading Eigen-Value = 1635 Loading Eigen-Value = 1636 Loading Eigen-Value = 1637 Loading Eigen-Value = 1638 Loading Eigen-Value = 1639 Loading Eigen-Value = 1640 Loading Eigen-Value = 1641 Loading Eigen-Value = 1642 Loading Eigen-Value = 1643 Loading Eigen-Value = 1644 Loading Eigen-Value = 1645 Loading Eigen-Value = 1646 Loading Eigen-Value = 1647 Loading Eigen-Value = 1648 Loading Eigen-Value = 1649 Loading Eigen-Value = 1650 Loading Eigen-Value = 1651 Loading Eigen-Value = 1652 Loading Eigen-Value = 1653 Loading Eigen-Value = 1654 Loading Eigen-Value = 1655 Loading Eigen-Value = 1656 Loading Eigen-Value = 1657 Loading Eigen-Value = 1658 Loading Eigen-Value = 1659 Loading Eigen-Value = 1660 Loading Eigen-Value = 1661 Loading Eigen-Value = 1662 Loading Eigen-Value = 1663 Loading Eigen-Value = 1664 Loading Eigen-Value = 1665 Loading Eigen-Value = 1666 Loading Eigen-Value = 1667 Loading Eigen-Value = 1668 Loading Eigen-Value = 1669 Loading Eigen-Value = 1670 Loading Eigen-Value = 1671 Loading Eigen-Value = 1672 Loading Eigen-Value = 1673 Loading Eigen-Value = 1674 Loading Eigen-Value = 1675 Loading Eigen-Value = 1676 Loading Eigen-Value = 1677 Loading Eigen-Value = 1678 Loading Eigen-Value = 1679 Loading Eigen-Value = 1680 Loading Eigen-Value = 1681 Loading Eigen-Value = 1682 Loading Eigen-Value = 1683 Loading Eigen-Value = 1684 Loading Eigen-Value = 1685 Loading Eigen-Value = 1686 Loading Eigen-Value = 1687 Loading Eigen-Value = 1688 Loading Eigen-Value = 1689 Loading Eigen-Value = 1690 Loading Eigen-Value = 1691 Loading Eigen-Value = 1692 Loading Eigen-Value = 1693 Loading Eigen-Value = 1694 Loading Eigen-Value = 1695 Loading Eigen-Value = 1696 Loading Eigen-Value = 1697 Loading Eigen-Value = 1698 Loading Eigen-Value = 1699 Loading Eigen-Value = 1700 Loading Eigen-Value = 1701 Loading Eigen-Value = 1702 Loading Eigen-Value = 1703 Loading Eigen-Value = 1704 Loading Eigen-Value = 1705 Loading Eigen-Value = 1706 Loading Eigen-Value = 1707 Loading Eigen-Value = 1708 Loading Eigen-Value = 1709 Loading Eigen-Value = 1710 Loading Eigen-Value = 1711 Loading Eigen-Value = 1712 Loading Eigen-Value = 1713 Loading Eigen-Value = 1714 Loading Eigen-Value = 1715 Loading Eigen-Value = 1716 Loading Eigen-Value = 1717 Loading Eigen-Value = 1718 Loading Eigen-Value = 1719 Loading Eigen-Value = 1720 Loading Eigen-Value = 1721 Loading Eigen-Value = 1722 Loading Eigen-Value = 1723 Loading Eigen-Value = 1724 Loading Eigen-Value = 1725 Loading Eigen-Value = 1726 Loading Eigen-Value = 1727 Loading Eigen-Value = 1728 Loading Eigen-Value = 1729 Loading Eigen-Value = 1730 Loading Eigen-Value = 1731 Loading Eigen-Value = 1732 Loading Eigen-Value = 1733 Loading Eigen-Value = 1734 Loading Eigen-Value = 1735 Loading Eigen-Value = 1736 Loading Eigen-Value = 1737 Loading Eigen-Value = 1738 Loading Eigen-Value = 1739 Loading Eigen-Value = 1740 Loading Eigen-Value = 1741 Loading Eigen-Value = 1742 Loading Eigen-Value = 1743 Loading Eigen-Value = 1744 Loading Eigen-Value = 1745 Loading Eigen-Value = 1746 Loading Eigen-Value = 1747 Loading Eigen-Value = 1748 Loading Eigen-Value = 1749 Loading Eigen-Value = 1750 Loading Eigen-Value = 1751 Loading Eigen-Value = 1752 Loading Eigen-Value = 1753 Loading Eigen-Value = 1754 Loading Eigen-Value = 1755 Loading Eigen-Value = 1756 Loading Eigen-Value = 1757 Loading Eigen-Value = 1758 Loading Eigen-Value = 1759 Loading Eigen-Value = 1760 Loading Eigen-Value = 1761 Loading Eigen-Value = 1762 Loading Eigen-Value = 1763 Loading Eigen-Value = 1764 Loading Eigen-Value = 1765 Loading Eigen-Value = 1766 Loading Eigen-Value = 1767 Loading Eigen-Value = 1768 Loading Eigen-Value = 1769 Loading Eigen-Value = 1770 Loading Eigen-Value = 1771 Loading Eigen-Value = 1772 Loading Eigen-Value = 1773 Loading Eigen-Value = 1774 Loading Eigen-Value = 1775 Loading Eigen-Value = 1776 Loading Eigen-Value = 1777 Loading Eigen-Value = 1778 Loading Eigen-Value = 1779 Natural freq (Mode 1) = 5.91752 (Hz) Natural freq (Mode 2) = 29.92398 (Hz) Natural freq (Mode 3) = 40.01939 (Hz) Natural freq (Mode 4) = 78.26336 (Hz) Natural freq (Mode 5) = 102.48770 (Hz) Natural freq (Mode 6) = 148.28700 (Hz) Natural freq (Mode 7) = 182.97520 (Hz) Natural freq (Mode 8) = 238.39370 (Hz) Natural freq (Mode 9) = 285.36330 (Hz) Natural freq (Mode 10) = 321.90370 (Hz) Natural freq (Mode 11) = 338.36210 (Hz) Natural freq (Mode 12) = 347.87480 (Hz) Natural freq (Mode 13) = 412.76490 (Hz) Natural freq (Mode 14) = 446.89790 (Hz) Natural freq (Mode 15) = 477.26050 (Hz) Natural freq (Mode 16) = 556.73130 (Hz) Natural freq (Mode 17) = 582.55570 (Hz) Natural freq (Mode 18) = 627.20430 (Hz) Natural freq (Mode 19) = 696.67300 (Hz) Natural freq (Mode 20) = 750.94670 (Hz) Natural freq (Mode 21) = 757.10910 (Hz) Natural freq (Mode 22) = 797.86110 (Hz) Natural freq (Mode 23) = 847.03330 (Hz) Natural freq (Mode 24) = 944.72760 (Hz) Natural freq (Mode 25) = 956.33970 (Hz) Natural freq (Mode 26) = 978.56320 (Hz) Natural freq (Mode 27) = 1011.29500 (Hz) Natural freq (Mode 28) = 1121.40300 (Hz) Natural freq (Mode 29) = 1155.17800 (Hz) Natural freq (Mode 30) = 1174.22000 (Hz) Natural freq (Mode 31) = 1218.32400 (Hz) Natural freq (Mode 32) = 1289.59300 (Hz) Natural freq (Mode 33) = 1300.85200 (Hz) Natural freq (Mode 34) = 1332.20600 (Hz) Natural freq (Mode 35) = 1359.39700 (Hz) Natural freq (Mode 36) = 1412.35900 (Hz) Natural freq (Mode 37) = 1457.87000 (Hz) Natural freq (Mode 38) = 1504.80200 (Hz) Natural freq (Mode 39) = 1555.90000 (Hz) Natural freq (Mode 40) = 1607.07800 (Hz) Natural freq (Mode 41) = 1655.47400 (Hz) Natural freq (Mode 42) = 1717.08000 (Hz) Natural freq (Mode 43) = 1741.97300 (Hz) Natural freq (Mode 44) = 1801.38700 (Hz) Natural freq (Mode 45) = 1873.31100 (Hz) Natural freq (Mode 46) = 1913.09800 (Hz) Natural freq (Mode 47) = 1980.26900 (Hz) Natural freq (Mode 48) = 1991.99800 (Hz) Natural freq (Mode 49) = 2069.91300 (Hz) Natural freq (Mode 50) = 2113.76400 (Hz) Natural freq (Mode 51) = 2145.78500 (Hz) Natural freq (Mode 52) = 2175.50900 (Hz) Natural freq (Mode 53) = 2224.13400 (Hz) Natural freq (Mode 54) = 2298.75800 (Hz) Natural freq (Mode 55) = 2349.76500 (Hz) Natural freq (Mode 56) = 2413.31600 (Hz) Natural freq (Mode 57) = 2439.34000 (Hz) Natural freq (Mode 58) = 2497.21500 (Hz) Natural freq (Mode 59) = 2499.99000 (Hz) Natural freq (Mode 60) = 2549.47200 (Hz) Natural freq (Mode 61) = 2608.88800 (Hz) Natural freq (Mode 62) = 2632.75600 (Hz) Natural freq (Mode 63) = 2710.43000 (Hz) Natural freq (Mode 64) = 2747.45500 (Hz) Natural freq (Mode 65) = 2787.56600 (Hz) Natural freq (Mode 66) = 2804.88200 (Hz) Natural freq (Mode 67) = 2828.01000 (Hz) Natural freq (Mode 68) = 2891.33900 (Hz) Natural freq (Mode 69) = 2943.88700 (Hz) Natural freq (Mode 70) = 2996.34500 (Hz) Natural freq (Mode 71) = 3038.47900 (Hz) Natural freq (Mode 72) = 3110.97300 (Hz) Natural freq (Mode 73) = 3155.74800 (Hz) Natural freq (Mode 74) = 3171.54500 (Hz) Natural freq (Mode 75) = 3208.80000 (Hz) Natural freq (Mode 76) = 3270.76600 (Hz) Natural freq (Mode 77) = 3337.48000 (Hz) Natural freq (Mode 78) = 3397.62800 (Hz) Natural freq (Mode 79) = 3430.15700 (Hz) Natural freq (Mode 80) = 3486.27900 (Hz) Natural freq (Mode 81) = 3519.90500 (Hz) Natural freq (Mode 82) = 3582.41700 (Hz) Natural freq (Mode 83) = 3644.34000 (Hz) Natural freq (Mode 84) = 3690.50500 (Hz) Natural freq (Mode 85) = 3709.94700 (Hz) Natural freq (Mode 86) = 3751.86800 (Hz) Natural freq (Mode 87) = 3847.60300 (Hz) Natural freq (Mode 88) = 3881.69700 (Hz) Natural freq (Mode 89) = 3929.56900 (Hz) Natural freq (Mode 90) = 4030.33000 (Hz) Natural freq (Mode 91) = 4075.24600 (Hz) Natural freq (Mode 92) = 4112.23100 (Hz) Natural freq (Mode 93) = 4125.08800 (Hz) Natural freq (Mode 94) = 4175.94300 (Hz) Natural freq (Mode 95) = 4249.31900 (Hz) Natural freq (Mode 96) = 4326.93400 (Hz) Natural freq (Mode 97) = 4350.07800 (Hz) Natural freq (Mode 98) = 4422.66200 (Hz) Natural freq (Mode 99) = 4433.83300 (Hz) Natural freq (Mode 100) = 4490.80200 (Hz) Natural freq (Mode 101) = 4533.85600 (Hz) Natural freq (Mode 102) = 4575.81800 (Hz) Natural freq (Mode 103) = 4650.17200 (Hz) Natural freq (Mode 104) = 4653.01800 (Hz) Natural freq (Mode 105) = 4762.06400 (Hz) Natural freq (Mode 106) = 4783.26800 (Hz) Natural freq (Mode 107) = 4833.77500 (Hz) Natural freq (Mode 108) = 4859.19300 (Hz) Natural freq (Mode 109) = 4906.46000 (Hz) Natural freq (Mode 110) = 4983.49100 (Hz) Natural freq (Mode 111) = 5036.52400 (Hz) Natural freq (Mode 112) = 5088.89300 (Hz) Natural freq (Mode 113) = 5131.49800 (Hz) Natural freq (Mode 114) = 5189.45600 (Hz) Natural freq (Mode 115) = 5226.69000 (Hz) Natural freq (Mode 116) = 5312.39900 (Hz) Natural freq (Mode 117) = 5337.54300 (Hz) Natural freq (Mode 118) = 5412.15200 (Hz) Natural freq (Mode 119) = 5468.34800 (Hz) Natural freq (Mode 120) = 5515.48600 (Hz) Natural freq (Mode 121) = 5524.08000 (Hz) Natural freq (Mode 122) = 5619.29500 (Hz) Natural freq (Mode 123) = 5653.70400 (Hz) Natural freq (Mode 124) = 5733.63600 (Hz) Natural freq (Mode 125) = 5773.94900 (Hz) Natural freq (Mode 126) = 5844.35200 (Hz) Natural freq (Mode 127) = 5867.65000 (Hz) Natural freq (Mode 128) = 5906.70100 (Hz) Natural freq (Mode 129) = 5971.92900 (Hz) Natural freq (Mode 130) = 6009.02100 (Hz) Natural freq (Mode 131) = 6072.23100 (Hz) Natural freq (Mode 132) = 6114.32400 (Hz) Natural freq (Mode 133) = 6217.45300 (Hz) Natural freq (Mode 134) = 6258.33500 (Hz) Natural freq (Mode 135) = 6280.35900 (Hz) Natural freq (Mode 136) = 6328.06800 (Hz) Natural freq (Mode 137) = 6380.03600 (Hz) Natural freq (Mode 138) = 6420.51900 (Hz) Natural freq (Mode 139) = 6443.62300 (Hz) Natural freq (Mode 140) = 6482.95600 (Hz) Natural freq (Mode 141) = 6556.30700 (Hz) Natural freq (Mode 142) = 6581.93700 (Hz) Natural freq (Mode 143) = 6681.89000 (Hz) Natural freq (Mode 144) = 6710.49400 (Hz) Natural freq (Mode 145) = 6712.56300 (Hz) Natural freq (Mode 146) = 6757.85200 (Hz) Natural freq (Mode 147) = 6773.85300 (Hz) Natural freq (Mode 148) = 6855.24800 (Hz) Natural freq (Mode 149) = 6906.85000 (Hz) Natural freq (Mode 150) = 6964.86500 (Hz) Natural freq (Mode 151) = 7005.47200 (Hz) Natural freq (Mode 152) = 7093.12700 (Hz) Natural freq (Mode 153) = 7172.58500 (Hz) Natural freq (Mode 154) = 7235.36700 (Hz) Natural freq (Mode 155) = 7284.38800 (Hz) Natural freq (Mode 156) = 7339.50900 (Hz) Natural freq (Mode 157) = 7387.76000 (Hz) Natural freq (Mode 158) = 7432.07800 (Hz) Natural freq (Mode 159) = 7484.19100 (Hz) Natural freq (Mode 160) = 7505.65500 (Hz) Natural freq (Mode 161) = 7575.40800 (Hz) Natural freq (Mode 162) = 7619.31300 (Hz) Natural freq (Mode 163) = 7645.70400 (Hz) Natural freq (Mode 164) = 7763.99600 (Hz) Natural freq (Mode 165) = 7804.56500 (Hz) Natural freq (Mode 166) = 7847.62900 (Hz) Natural freq (Mode 167) = 7884.94000 (Hz) Natural freq (Mode 168) = 7971.14100 (Hz) Natural freq (Mode 169) = 7981.26000 (Hz) Natural freq (Mode 170) = 8018.25500 (Hz) Natural freq (Mode 171) = 8065.35200 (Hz) Natural freq (Mode 172) = 8190.58300 (Hz) Natural freq (Mode 173) = 8219.15300 (Hz) Natural freq (Mode 174) = 8242.49900 (Hz) Natural freq (Mode 175) = 8305.01600 (Hz) Natural freq (Mode 176) = 8338.74300 (Hz) Natural freq (Mode 177) = 8449.34200 (Hz) Natural freq (Mode 178) = 8515.47200 (Hz) Natural freq (Mode 179) = 8589.43700 (Hz) Natural freq (Mode 180) = 8616.56100 (Hz) Natural freq (Mode 181) = 8640.13700 (Hz) Natural freq (Mode 182) = 8712.28800 (Hz) Natural freq (Mode 183) = 8716.81500 (Hz) Natural freq (Mode 184) = 8787.58300 (Hz) Natural freq (Mode 185) = 8846.56900 (Hz) Natural freq (Mode 186) = 8875.50500 (Hz) Natural freq (Mode 187) = 8964.94700 (Hz) Natural freq (Mode 188) = 8992.86500 (Hz) Natural freq (Mode 189) = 9077.22400 (Hz) Natural freq (Mode 190) = 9096.26100 (Hz) Natural freq (Mode 191) = 9145.99500 (Hz) Natural freq (Mode 192) = 9199.71100 (Hz) Natural freq (Mode 193) = 9239.19700 (Hz) Natural freq (Mode 194) = 9335.28900 (Hz) Natural freq (Mode 195) = 9367.16700 (Hz) Natural freq (Mode 196) = 9496.20700 (Hz) Natural freq (Mode 197) = 9506.20900 (Hz) Natural freq (Mode 198) = 9530.04800 (Hz) Natural freq (Mode 199) = 9569.59000 (Hz) Natural freq (Mode 200) = 9612.48400 (Hz) Natural freq (Mode 201) = 9670.18300 (Hz) Natural freq (Mode 202) = 9702.23300 (Hz) Natural freq (Mode 203) = 9772.30000 (Hz) Natural freq (Mode 204) = 9825.17600 (Hz) Natural freq (Mode 205) = 9883.47700 (Hz) Natural freq (Mode 206) = 9901.35100 (Hz) Natural freq (Mode 207) = 9952.14500 (Hz) Natural freq (Mode 208) = 10096.61000 (Hz) Natural freq (Mode 209) = 10117.51000 (Hz) Natural freq (Mode 210) = 10152.60000 (Hz) Natural freq (Mode 211) = 10241.89000 (Hz) Natural freq (Mode 212) = 10283.19000 (Hz) Natural freq (Mode 213) = 10290.01000 (Hz) Natural freq (Mode 214) = 10313.76000 (Hz) Natural freq (Mode 215) = 10380.63000 (Hz) Natural freq (Mode 216) = 10423.29000 (Hz) Natural freq (Mode 217) = 10489.16000 (Hz) Natural freq (Mode 218) = 10534.94000 (Hz) Natural freq (Mode 219) = 10617.34000 (Hz) Natural freq (Mode 220) = 10692.66000 (Hz) Natural freq (Mode 221) = 10724.57000 (Hz) Natural freq (Mode 222) = 10783.30000 (Hz) Natural freq (Mode 223) = 10796.14000 (Hz) Natural freq (Mode 224) = 10837.42000 (Hz) Natural freq (Mode 225) = 10917.22000 (Hz) Natural freq (Mode 226) = 10990.39000 (Hz) Natural freq (Mode 227) = 11032.01000 (Hz) Natural freq (Mode 228) = 11066.56000 (Hz) Natural freq (Mode 229) = 11107.64000 (Hz) Natural freq (Mode 230) = 11181.18000 (Hz) Natural freq (Mode 231) = 11203.75000 (Hz) Natural freq (Mode 232) = 11301.06000 (Hz) Natural freq (Mode 233) = 11368.84000 (Hz) Natural freq (Mode 234) = 11405.65000 (Hz) Natural freq (Mode 235) = 11479.89000 (Hz) Natural freq (Mode 236) = 11556.38000 (Hz) Natural freq (Mode 237) = 11582.24000 (Hz) Natural freq (Mode 238) = 11608.71000 (Hz) Natural freq (Mode 239) = 11663.11000 (Hz) Natural freq (Mode 240) = 11767.24000 (Hz) Natural freq (Mode 241) = 11809.88000 (Hz) Natural freq (Mode 242) = 11869.78000 (Hz) Natural freq (Mode 243) = 11968.82000 (Hz) Natural freq (Mode 244) = 11983.42000 (Hz) Natural freq (Mode 245) = 12042.58000 (Hz) Natural freq (Mode 246) = 12116.63000 (Hz) Natural freq (Mode 247) = 12143.37000 (Hz) Natural freq (Mode 248) = 12143.61000 (Hz) Natural freq (Mode 249) = 12189.26000 (Hz) Natural freq (Mode 250) = 12256.66000 (Hz) Natural freq (Mode 251) = 12310.75000 (Hz) Natural freq (Mode 252) = 12364.03000 (Hz) Natural freq (Mode 253) = 12370.65000 (Hz) Natural freq (Mode 254) = 12548.26000 (Hz) Natural freq (Mode 255) = 12565.68000 (Hz) Natural freq (Mode 256) = 12594.88000 (Hz) Natural freq (Mode 257) = 12712.07000 (Hz) Natural freq (Mode 258) = 12770.17000 (Hz) Natural freq (Mode 259) = 12775.62000 (Hz) Natural freq (Mode 260) = 12825.19000 (Hz) Natural freq (Mode 261) = 12905.15000 (Hz) Natural freq (Mode 262) = 12955.70000 (Hz) Natural freq (Mode 263) = 13036.73000 (Hz) Natural freq (Mode 264) = 13054.72000 (Hz) Natural freq (Mode 265) = 13161.42000 (Hz) Natural freq (Mode 266) = 13192.61000 (Hz) Natural freq (Mode 267) = 13239.57000 (Hz) Natural freq (Mode 268) = 13284.37000 (Hz) Natural freq (Mode 269) = 13384.14000 (Hz) Natural freq (Mode 270) = 13408.39000 (Hz) Natural freq (Mode 271) = 13456.16000 (Hz) Natural freq (Mode 272) = 13472.22000 (Hz) Natural freq (Mode 273) = 13530.73000 (Hz) Natural freq (Mode 274) = 13593.85000 (Hz) Natural freq (Mode 275) = 13760.49000 (Hz) Natural freq (Mode 276) = 13785.68000 (Hz) Natural freq (Mode 277) = 13876.39000 (Hz) Natural freq (Mode 278) = 13897.87000 (Hz) Natural freq (Mode 279) = 13949.89000 (Hz) Natural freq (Mode 280) = 13982.83000 (Hz) Natural freq (Mode 281) = 14036.06000 (Hz) Natural freq (Mode 282) = 14061.26000 (Hz) Natural freq (Mode 283) = 14126.31000 (Hz) Natural freq (Mode 284) = 14289.37000 (Hz) Natural freq (Mode 285) = 14326.99000 (Hz) Natural freq (Mode 286) = 14398.55000 (Hz) Natural freq (Mode 287) = 14484.76000 (Hz) Natural freq (Mode 288) = 14489.28000 (Hz) Natural freq (Mode 289) = 14522.37000 (Hz) Natural freq (Mode 290) = 14565.89000 (Hz) Natural freq (Mode 291) = 14606.46000 (Hz) Natural freq (Mode 292) = 14649.44000 (Hz) Natural freq (Mode 293) = 14786.59000 (Hz) Natural freq (Mode 294) = 14893.02000 (Hz) Natural freq (Mode 295) = 14975.89000 (Hz) Natural freq (Mode 296) = 14990.37000 (Hz) Natural freq (Mode 297) = 15048.04000 (Hz) Natural freq (Mode 298) = 15137.92000 (Hz) Natural freq (Mode 299) = 15180.15000 (Hz) Natural freq (Mode 300) = 15208.71000 (Hz) Natural freq (Mode 301) = 15324.33000 (Hz) Natural freq (Mode 302) = 15358.41000 (Hz) Natural freq (Mode 303) = 15371.80000 (Hz) Natural freq (Mode 304) = 15469.29000 (Hz) Natural freq (Mode 305) = 15502.22000 (Hz) Natural freq (Mode 306) = 15582.06000 (Hz) Natural freq (Mode 307) = 15697.16000 (Hz) Natural freq (Mode 308) = 15716.81000 (Hz) Natural freq (Mode 309) = 15838.63000 (Hz) Natural freq (Mode 310) = 15881.20000 (Hz) Natural freq (Mode 311) = 15983.89000 (Hz) Natural freq (Mode 312) = 15994.51000 (Hz) Natural freq (Mode 313) = 16002.53000 (Hz) Natural freq (Mode 314) = 16137.48000 (Hz) Natural freq (Mode 315) = 16143.49000 (Hz) Natural freq (Mode 316) = 16191.25000 (Hz) Natural freq (Mode 317) = 16444.55000 (Hz) Natural freq (Mode 318) = 16465.20000 (Hz) Natural freq (Mode 319) = 16540.14000 (Hz) Natural freq (Mode 320) = 16545.05000 (Hz) Natural freq (Mode 321) = 16607.63000 (Hz) Natural freq (Mode 322) = 16787.41000 (Hz) Natural freq (Mode 323) = 16809.01000 (Hz) Natural freq (Mode 324) = 16854.44000 (Hz) Natural freq (Mode 325) = 16898.50000 (Hz) Natural freq (Mode 326) = 16931.53000 (Hz) Natural freq (Mode 327) = 16952.62000 (Hz) Natural freq (Mode 328) = 17074.71000 (Hz) Natural freq (Mode 329) = 17099.57000 (Hz) Natural freq (Mode 330) = 17119.86000 (Hz) Natural freq (Mode 331) = 17222.80000 (Hz) Natural freq (Mode 332) = 17266.61000 (Hz) Natural freq (Mode 333) = 17383.30000 (Hz) Natural freq (Mode 334) = 17418.65000 (Hz) Natural freq (Mode 335) = 17488.28000 (Hz) Natural freq (Mode 336) = 17541.06000 (Hz) Natural freq (Mode 337) = 17694.88000 (Hz) Natural freq (Mode 338) = 17700.81000 (Hz) Natural freq (Mode 339) = 17741.71000 (Hz) Natural freq (Mode 340) = 17800.10000 (Hz) Natural freq (Mode 341) = 17816.33000 (Hz) Natural freq (Mode 342) = 17925.23000 (Hz) Natural freq (Mode 343) = 17964.70000 (Hz) Natural freq (Mode 344) = 18050.17000 (Hz) Natural freq (Mode 345) = 18098.53000 (Hz) Natural freq (Mode 346) = 18131.22000 (Hz) Natural freq (Mode 347) = 18183.38000 (Hz) Natural freq (Mode 348) = 18215.32000 (Hz) Natural freq (Mode 349) = 18334.29000 (Hz) Natural freq (Mode 350) = 18362.53000 (Hz) Natural freq (Mode 351) = 18486.87000 (Hz) Natural freq (Mode 352) = 18591.83000 (Hz) Natural freq (Mode 353) = 18709.08000 (Hz) Natural freq (Mode 354) = 18712.34000 (Hz) Natural freq (Mode 355) = 18799.42000 (Hz) Natural freq (Mode 356) = 18829.22000 (Hz) Natural freq (Mode 357) = 18853.39000 (Hz) Natural freq (Mode 358) = 18976.00000 (Hz) Natural freq (Mode 359) = 19059.20000 (Hz) Natural freq (Mode 360) = 19125.02000 (Hz) Natural freq (Mode 361) = 19157.08000 (Hz) Natural freq (Mode 362) = 19255.37000 (Hz) Natural freq (Mode 363) = 19304.60000 (Hz) Natural freq (Mode 364) = 19419.35000 (Hz) Natural freq (Mode 365) = 19455.45000 (Hz) Natural freq (Mode 366) = 19511.95000 (Hz) Natural freq (Mode 367) = 19591.56000 (Hz) Natural freq (Mode 368) = 19646.65000 (Hz) Natural freq (Mode 369) = 19757.04000 (Hz) Natural freq (Mode 370) = 19782.00000 (Hz) Natural freq (Mode 371) = 19921.47000 (Hz) Natural freq (Mode 372) = 20038.24000 (Hz) Natural freq (Mode 373) = 20087.59000 (Hz) Natural freq (Mode 374) = 20247.26000 (Hz) Natural freq (Mode 375) = 20314.55000 (Hz) Natural freq (Mode 376) = 20347.61000 (Hz) Natural freq (Mode 377) = 20409.15000 (Hz) Natural freq (Mode 378) = 20555.38000 (Hz) Natural freq (Mode 379) = 20745.27000 (Hz) Natural freq (Mode 380) = 20826.08000 (Hz) Natural freq (Mode 381) = 20926.47000 (Hz) Natural freq (Mode 382) = 20927.93000 (Hz) Natural freq (Mode 383) = 20961.74000 (Hz) Natural freq (Mode 384) = 21049.74000 (Hz) Natural freq (Mode 385) = 21086.09000 (Hz) Natural freq (Mode 386) = 21226.15000 (Hz) Natural freq (Mode 387) = 21285.19000 (Hz) Natural freq (Mode 388) = 21322.08000 (Hz) Natural freq (Mode 389) = 21443.02000 (Hz) Natural freq (Mode 390) = 21485.59000 (Hz) Natural freq (Mode 391) = 21498.71000 (Hz) Natural freq (Mode 392) = 21600.59000 (Hz) Natural freq (Mode 393) = 21699.40000 (Hz) Natural freq (Mode 394) = 21749.01000 (Hz) Natural freq (Mode 395) = 21760.19000 (Hz) Natural freq (Mode 396) = 21871.83000 (Hz) Natural freq (Mode 397) = 21968.82000 (Hz) Natural freq (Mode 398) = 22004.93000 (Hz) Natural freq (Mode 399) = 22037.06000 (Hz) Natural freq (Mode 400) = 22132.05000 (Hz) Natural freq (Mode 401) = 22272.75000 (Hz) Natural freq (Mode 402) = 22284.71000 (Hz) Natural freq (Mode 403) = 22343.19000 (Hz) Natural freq (Mode 404) = 22492.85000 (Hz) Natural freq (Mode 405) = 22675.22000 (Hz) Natural freq (Mode 406) = 22726.67000 (Hz) Natural freq (Mode 407) = 22795.38000 (Hz) Natural freq (Mode 408) = 22847.12000 (Hz) Natural freq (Mode 409) = 23027.21000 (Hz) Natural freq (Mode 410) = 23066.16000 (Hz) Natural freq (Mode 411) = 23111.55000 (Hz) Natural freq (Mode 412) = 23264.07000 (Hz) Natural freq (Mode 413) = 23277.39000 (Hz) Natural freq (Mode 414) = 23280.87000 (Hz) Natural freq (Mode 415) = 23489.27000 (Hz) Natural freq (Mode 416) = 23508.29000 (Hz) Natural freq (Mode 417) = 23538.90000 (Hz) Natural freq (Mode 418) = 23734.87000 (Hz) Natural freq (Mode 419) = 23748.21000 (Hz) Natural freq (Mode 420) = 23776.47000 (Hz) Natural freq (Mode 421) = 23836.88000 (Hz) Natural freq (Mode 422) = 23851.33000 (Hz) Natural freq (Mode 423) = 23996.21000 (Hz) Natural freq (Mode 424) = 24072.71000 (Hz) Natural freq (Mode 425) = 24231.38000 (Hz) Natural freq (Mode 426) = 24326.89000 (Hz) Natural freq (Mode 427) = 24335.46000 (Hz) Natural freq (Mode 428) = 24378.13000 (Hz) Natural freq (Mode 429) = 24422.91000 (Hz) Natural freq (Mode 430) = 24535.55000 (Hz) Natural freq (Mode 431) = 24612.28000 (Hz) Natural freq (Mode 432) = 24749.69000 (Hz) Natural freq (Mode 433) = 24864.25000 (Hz) Natural freq (Mode 434) = 25020.23000 (Hz) Natural freq (Mode 435) = 25036.26000 (Hz) Natural freq (Mode 436) = 25255.07000 (Hz) Natural freq (Mode 437) = 25348.07000 (Hz) Natural freq (Mode 438) = 25376.09000 (Hz) Natural freq (Mode 439) = 25408.28000 (Hz) Natural freq (Mode 440) = 25484.80000 (Hz) Natural freq (Mode 441) = 25615.76000 (Hz) Natural freq (Mode 442) = 25669.87000 (Hz) Natural freq (Mode 443) = 25819.13000 (Hz) Natural freq (Mode 444) = 25981.25000 (Hz) Natural freq (Mode 445) = 25999.63000 (Hz) Natural freq (Mode 446) = 26070.56000 (Hz) Natural freq (Mode 447) = 26145.77000 (Hz) Natural freq (Mode 448) = 26279.59000 (Hz) Natural freq (Mode 449) = 26351.51000 (Hz) Natural freq (Mode 450) = 26395.38000 (Hz) Natural freq (Mode 451) = 26502.02000 (Hz) Natural freq (Mode 452) = 26532.53000 (Hz) Natural freq (Mode 453) = 26637.85000 (Hz) Natural freq (Mode 454) = 26643.48000 (Hz) Natural freq (Mode 455) = 26745.91000 (Hz) Natural freq (Mode 456) = 26934.27000 (Hz) Natural freq (Mode 457) = 27070.38000 (Hz) Natural freq (Mode 458) = 27164.86000 (Hz) Natural freq (Mode 459) = 27237.99000 (Hz) Natural freq (Mode 460) = 27380.39000 (Hz) Natural freq (Mode 461) = 27500.71000 (Hz) Natural freq (Mode 462) = 27556.49000 (Hz) Natural freq (Mode 463) = 27702.19000 (Hz) Natural freq (Mode 464) = 27702.94000 (Hz) Natural freq (Mode 465) = 27916.39000 (Hz) Natural freq (Mode 466) = 28012.95000 (Hz) Natural freq (Mode 467) = 28161.58000 (Hz) Natural freq (Mode 468) = 28179.12000 (Hz) Natural freq (Mode 469) = 28422.62000 (Hz) Natural freq (Mode 470) = 28474.77000 (Hz) Natural freq (Mode 471) = 28560.92000 (Hz) Natural freq (Mode 472) = 28566.15000 (Hz) Natural freq (Mode 473) = 28710.87000 (Hz) Natural freq (Mode 474) = 28781.45000 (Hz) Natural freq (Mode 475) = 28999.03000 (Hz) Natural freq (Mode 476) = 29078.86000 (Hz) Natural freq (Mode 477) = 29154.48000 (Hz) Natural freq (Mode 478) = 29296.92000 (Hz) Natural freq (Mode 479) = 29356.81000 (Hz) Natural freq (Mode 480) = 29380.71000 (Hz) Natural freq (Mode 481) = 29478.38000 (Hz) Natural freq (Mode 482) = 29553.13000 (Hz) Natural freq (Mode 483) = 29622.04000 (Hz) Natural freq (Mode 484) = 29712.53000 (Hz) Natural freq (Mode 485) = 30011.06000 (Hz) Natural freq (Mode 486) = 30035.66000 (Hz) Natural freq (Mode 487) = 30102.46000 (Hz) Natural freq (Mode 488) = 30209.47000 (Hz) Natural freq (Mode 489) = 30280.31000 (Hz) Natural freq (Mode 490) = 30323.96000 (Hz) Natural freq (Mode 491) = 30365.31000 (Hz) Natural freq (Mode 492) = 30520.68000 (Hz) Natural freq (Mode 493) = 30541.57000 (Hz) Natural freq (Mode 494) = 30606.26000 (Hz) Natural freq (Mode 495) = 30742.72000 (Hz) Natural freq (Mode 496) = 30869.45000 (Hz) Natural freq (Mode 497) = 30969.95000 (Hz) Natural freq (Mode 498) = 31100.58000 (Hz) Natural freq (Mode 499) = 31169.65000 (Hz) Natural freq (Mode 500) = 31244.07000 (Hz) Natural freq (Mode 501) = 31425.86000 (Hz) Natural freq (Mode 502) = 31537.51000 (Hz) Natural freq (Mode 503) = 31639.96000 (Hz) Natural freq (Mode 504) = 31754.34000 (Hz) Natural freq (Mode 505) = 31760.84000 (Hz) Natural freq (Mode 506) = 31883.20000 (Hz) Natural freq (Mode 507) = 32002.92000 (Hz) Natural freq (Mode 508) = 32220.74000 (Hz) Natural freq (Mode 509) = 32290.88000 (Hz) Natural freq (Mode 510) = 32391.40000 (Hz) Natural freq (Mode 511) = 32608.03000 (Hz) Natural freq (Mode 512) = 32647.91000 (Hz) Natural freq (Mode 513) = 32720.89000 (Hz) Natural freq (Mode 514) = 32949.41000 (Hz) Natural freq (Mode 515) = 32988.75000 (Hz) Natural freq (Mode 516) = 33115.60000 (Hz) Natural freq (Mode 517) = 33200.03000 (Hz) Natural freq (Mode 518) = 33318.92000 (Hz) Natural freq (Mode 519) = 33330.25000 (Hz) Natural freq (Mode 520) = 33333.78000 (Hz) Natural freq (Mode 521) = 33486.56000 (Hz) Natural freq (Mode 522) = 33531.17000 (Hz) Natural freq (Mode 523) = 33683.28000 (Hz) Natural freq (Mode 524) = 33797.57000 (Hz) Natural freq (Mode 525) = 33906.94000 (Hz) Natural freq (Mode 526) = 33914.80000 (Hz) Natural freq (Mode 527) = 33989.41000 (Hz) Natural freq (Mode 528) = 34210.63000 (Hz) Natural freq (Mode 529) = 34378.73000 (Hz) Natural freq (Mode 530) = 34494.40000 (Hz) Natural freq (Mode 531) = 34582.28000 (Hz) Natural freq (Mode 532) = 34836.82000 (Hz) Natural freq (Mode 533) = 34902.17000 (Hz) Natural freq (Mode 534) = 34987.61000 (Hz) Natural freq (Mode 535) = 35067.79000 (Hz) Natural freq (Mode 536) = 35153.96000 (Hz) Natural freq (Mode 537) = 35173.18000 (Hz) Natural freq (Mode 538) = 35315.79000 (Hz) Natural freq (Mode 539) = 35452.04000 (Hz) Natural freq (Mode 540) = 35564.39000 (Hz) Natural freq (Mode 541) = 35577.60000 (Hz) Natural freq (Mode 542) = 35671.63000 (Hz) Natural freq (Mode 543) = 35764.36000 (Hz) Natural freq (Mode 544) = 35817.39000 (Hz) Natural freq (Mode 545) = 35987.39000 (Hz) Natural freq (Mode 546) = 35988.65000 (Hz) Natural freq (Mode 547) = 36149.87000 (Hz) Natural freq (Mode 548) = 36216.11000 (Hz) Natural freq (Mode 549) = 36374.59000 (Hz) Natural freq (Mode 550) = 36456.40000 (Hz) Natural freq (Mode 551) = 36643.81000 (Hz) Natural freq (Mode 552) = 36841.90000 (Hz) Natural freq (Mode 553) = 36898.49000 (Hz) Natural freq (Mode 554) = 36940.48000 (Hz) Natural freq (Mode 555) = 37109.42000 (Hz) Natural freq (Mode 556) = 37109.45000 (Hz) Natural freq (Mode 557) = 37157.88000 (Hz) Natural freq (Mode 558) = 37177.07000 (Hz) Natural freq (Mode 559) = 37287.62000 (Hz) Natural freq (Mode 560) = 37387.53000 (Hz) Natural freq (Mode 561) = 37522.76000 (Hz) Natural freq (Mode 562) = 37628.77000 (Hz) Natural freq (Mode 563) = 37734.15000 (Hz) Natural freq (Mode 564) = 37824.32000 (Hz) Natural freq (Mode 565) = 37936.66000 (Hz) Natural freq (Mode 566) = 38054.42000 (Hz) Natural freq (Mode 567) = 38287.95000 (Hz) Natural freq (Mode 568) = 38432.25000 (Hz) Natural freq (Mode 569) = 38489.84000 (Hz) Natural freq (Mode 570) = 38652.49000 (Hz) Natural freq (Mode 571) = 38702.59000 (Hz) Natural freq (Mode 572) = 38877.29000 (Hz) Natural freq (Mode 573) = 39004.32000 (Hz) Natural freq (Mode 574) = 39191.21000 (Hz) Natural freq (Mode 575) = 39286.07000 (Hz) Natural freq (Mode 576) = 39329.37000 (Hz) Natural freq (Mode 577) = 39574.73000 (Hz) Natural freq (Mode 578) = 39720.89000 (Hz) Natural freq (Mode 579) = 40162.23000 (Hz) Natural freq (Mode 580) = 40253.22000 (Hz) Natural freq (Mode 581) = 40293.79000 (Hz) Natural freq (Mode 582) = 40337.32000 (Hz) Natural freq (Mode 583) = 40474.10000 (Hz) Natural freq (Mode 584) = 40602.31000 (Hz) Natural freq (Mode 585) = 40635.95000 (Hz) Natural freq (Mode 586) = 40660.85000 (Hz) Natural freq (Mode 587) = 40743.75000 (Hz) Natural freq (Mode 588) = 40756.84000 (Hz) Natural freq (Mode 589) = 40949.57000 (Hz) Natural freq (Mode 590) = 40995.24000 (Hz) Natural freq (Mode 591) = 41223.55000 (Hz) Natural freq (Mode 592) = 41359.39000 (Hz) Natural freq (Mode 593) = 41528.88000 (Hz) Natural freq (Mode 594) = 41791.72000 (Hz) Natural freq (Mode 595) = 41887.48000 (Hz) Natural freq (Mode 596) = 42118.45000 (Hz) Natural freq (Mode 597) = 42198.64000 (Hz) Natural freq (Mode 598) = 42348.55000 (Hz) Natural freq (Mode 599) = 42370.13000 (Hz) Natural freq (Mode 600) = 42416.97000 (Hz) Natural freq (Mode 601) = 42462.20000 (Hz) Natural freq (Mode 602) = 42642.21000 (Hz) Natural freq (Mode 603) = 42726.17000 (Hz) Natural freq (Mode 604) = 42854.97000 (Hz) Natural freq (Mode 605) = 42962.25000 (Hz) Natural freq (Mode 606) = 43123.13000 (Hz) Natural freq (Mode 607) = 43203.68000 (Hz) Natural freq (Mode 608) = 43400.77000 (Hz) Natural freq (Mode 609) = 43508.95000 (Hz) Natural freq (Mode 610) = 43597.38000 (Hz) Natural freq (Mode 611) = 43700.77000 (Hz) Natural freq (Mode 612) = 43704.76000 (Hz) Natural freq (Mode 613) = 43877.68000 (Hz) Natural freq (Mode 614) = 44012.25000 (Hz) Natural freq (Mode 615) = 44106.74000 (Hz) Natural freq (Mode 616) = 44292.90000 (Hz) Natural freq (Mode 617) = 44314.06000 (Hz) Natural freq (Mode 618) = 44374.05000 (Hz) Natural freq (Mode 619) = 44397.46000 (Hz) Natural freq (Mode 620) = 44586.68000 (Hz) Natural freq (Mode 621) = 44696.46000 (Hz) Natural freq (Mode 622) = 44741.60000 (Hz) Natural freq (Mode 623) = 45054.47000 (Hz) Natural freq (Mode 624) = 45140.14000 (Hz) Natural freq (Mode 625) = 45249.72000 (Hz) Natural freq (Mode 626) = 45385.59000 (Hz) Natural freq (Mode 627) = 45567.35000 (Hz) Natural freq (Mode 628) = 45605.37000 (Hz) Natural freq (Mode 629) = 45735.81000 (Hz) Natural freq (Mode 630) = 45752.43000 (Hz) Natural freq (Mode 631) = 46051.15000 (Hz) Natural freq (Mode 632) = 46420.19000 (Hz) Natural freq (Mode 633) = 46488.60000 (Hz) Natural freq (Mode 634) = 46552.35000 (Hz) Natural freq (Mode 635) = 46577.11000 (Hz) Natural freq (Mode 636) = 46578.90000 (Hz) Natural freq (Mode 637) = 46694.76000 (Hz) Natural freq (Mode 638) = 46912.64000 (Hz) Natural freq (Mode 639) = 46981.14000 (Hz) Natural freq (Mode 640) = 47193.58000 (Hz) Natural freq (Mode 641) = 47238.25000 (Hz) Natural freq (Mode 642) = 47338.20000 (Hz) Natural freq (Mode 643) = 47429.59000 (Hz) Natural freq (Mode 644) = 47576.44000 (Hz) Natural freq (Mode 645) = 47611.71000 (Hz) Natural freq (Mode 646) = 47691.93000 (Hz) Natural freq (Mode 647) = 47807.08000 (Hz) Natural freq (Mode 648) = 47890.22000 (Hz) Natural freq (Mode 649) = 47917.94000 (Hz) Natural freq (Mode 650) = 48003.06000 (Hz) Natural freq (Mode 651) = 48405.16000 (Hz) Natural freq (Mode 652) = 48501.56000 (Hz) Natural freq (Mode 653) = 48589.31000 (Hz) Natural freq (Mode 654) = 48598.45000 (Hz) Natural freq (Mode 655) = 48779.29000 (Hz) Natural freq (Mode 656) = 48883.09000 (Hz) Natural freq (Mode 657) = 48930.20000 (Hz) Natural freq (Mode 658) = 49088.71000 (Hz) Natural freq (Mode 659) = 49207.57000 (Hz) Natural freq (Mode 660) = 49256.51000 (Hz) Natural freq (Mode 661) = 49376.35000 (Hz) Natural freq (Mode 662) = 49480.93000 (Hz) Natural freq (Mode 663) = 49565.85000 (Hz) Natural freq (Mode 664) = 49718.37000 (Hz) Natural freq (Mode 665) = 49722.37000 (Hz) Natural freq (Mode 666) = 49790.09000 (Hz) Natural freq (Mode 667) = 49897.80000 (Hz) Natural freq (Mode 668) = 50054.08000 (Hz) Natural freq (Mode 669) = 50090.88000 (Hz) Natural freq (Mode 670) = 50160.08000 (Hz) Natural freq (Mode 671) = 50228.52000 (Hz) Natural freq (Mode 672) = 50465.21000 (Hz) Natural freq (Mode 673) = 50484.11000 (Hz) Natural freq (Mode 674) = 50692.21000 (Hz) Natural freq (Mode 675) = 50853.68000 (Hz) Natural freq (Mode 676) = 50857.21000 (Hz) Natural freq (Mode 677) = 50936.92000 (Hz) Natural freq (Mode 678) = 51135.05000 (Hz) Natural freq (Mode 679) = 51171.95000 (Hz) Natural freq (Mode 680) = 51382.60000 (Hz) Natural freq (Mode 681) = 51500.84000 (Hz) Natural freq (Mode 682) = 51551.45000 (Hz) Natural freq (Mode 683) = 51604.40000 (Hz) Natural freq (Mode 684) = 51794.87000 (Hz) Natural freq (Mode 685) = 51921.50000 (Hz) Natural freq (Mode 686) = 52077.61000 (Hz) Natural freq (Mode 687) = 52106.14000 (Hz) Natural freq (Mode 688) = 52156.48000 (Hz) Natural freq (Mode 689) = 52196.38000 (Hz) Natural freq (Mode 690) = 52375.95000 (Hz) Natural freq (Mode 691) = 52511.88000 (Hz) Natural freq (Mode 692) = 52690.02000 (Hz) Natural freq (Mode 693) = 52760.29000 (Hz) Natural freq (Mode 694) = 52983.51000 (Hz) Natural freq (Mode 695) = 53151.14000 (Hz) Natural freq (Mode 696) = 53168.78000 (Hz) Natural freq (Mode 697) = 53351.66000 (Hz) Natural freq (Mode 698) = 53457.94000 (Hz) Natural freq (Mode 699) = 53501.50000 (Hz) Natural freq (Mode 700) = 53568.66000 (Hz) Natural freq (Mode 701) = 53771.08000 (Hz) Natural freq (Mode 702) = 53815.28000 (Hz) Natural freq (Mode 703) = 53819.51000 (Hz) Natural freq (Mode 704) = 54018.69000 (Hz) Natural freq (Mode 705) = 54206.11000 (Hz) Natural freq (Mode 706) = 54242.44000 (Hz) Natural freq (Mode 707) = 54451.73000 (Hz) Natural freq (Mode 708) = 54504.73000 (Hz) Natural freq (Mode 709) = 54515.07000 (Hz) Natural freq (Mode 710) = 54603.34000 (Hz) Natural freq (Mode 711) = 54798.02000 (Hz) Natural freq (Mode 712) = 54826.34000 (Hz) Natural freq (Mode 713) = 54976.60000 (Hz) Natural freq (Mode 714) = 55099.90000 (Hz) Natural freq (Mode 715) = 55233.76000 (Hz) Natural freq (Mode 716) = 55312.55000 (Hz) Natural freq (Mode 717) = 55359.35000 (Hz) Natural freq (Mode 718) = 55622.14000 (Hz) Natural freq (Mode 719) = 55794.26000 (Hz) Natural freq (Mode 720) = 55892.18000 (Hz) Natural freq (Mode 721) = 56015.41000 (Hz) Natural freq (Mode 722) = 56088.41000 (Hz) Natural freq (Mode 723) = 56115.56000 (Hz) Natural freq (Mode 724) = 56334.32000 (Hz) Natural freq (Mode 725) = 56351.92000 (Hz) Natural freq (Mode 726) = 56609.43000 (Hz) Natural freq (Mode 727) = 56690.62000 (Hz) Natural freq (Mode 728) = 56781.62000 (Hz) Natural freq (Mode 729) = 56865.87000 (Hz) Natural freq (Mode 730) = 56948.31000 (Hz) Natural freq (Mode 731) = 57119.90000 (Hz) Natural freq (Mode 732) = 57228.48000 (Hz) Natural freq (Mode 733) = 57330.72000 (Hz) Natural freq (Mode 734) = 57473.44000 (Hz) Natural freq (Mode 735) = 57547.01000 (Hz) Natural freq (Mode 736) = 57627.58000 (Hz) Natural freq (Mode 737) = 57732.92000 (Hz) Natural freq (Mode 738) = 57822.45000 (Hz) Natural freq (Mode 739) = 57992.67000 (Hz) Natural freq (Mode 740) = 58178.70000 (Hz) Natural freq (Mode 741) = 58235.37000 (Hz) Natural freq (Mode 742) = 58342.95000 (Hz) Natural freq (Mode 743) = 58393.04000 (Hz) Natural freq (Mode 744) = 58548.01000 (Hz) Natural freq (Mode 745) = 58743.37000 (Hz) Natural freq (Mode 746) = 58747.77000 (Hz) Natural freq (Mode 747) = 58763.92000 (Hz) Natural freq (Mode 748) = 58967.43000 (Hz) Natural freq (Mode 749) = 59096.52000 (Hz) Natural freq (Mode 750) = 59102.65000 (Hz) Natural freq (Mode 751) = 59219.30000 (Hz) Natural freq (Mode 752) = 59386.15000 (Hz) Natural freq (Mode 753) = 59562.50000 (Hz) Natural freq (Mode 754) = 59631.56000 (Hz) Natural freq (Mode 755) = 59639.75000 (Hz) Natural freq (Mode 756) = 59712.64000 (Hz) Natural freq (Mode 757) = 59838.64000 (Hz) Natural freq (Mode 758) = 59903.59000 (Hz) Natural freq (Mode 759) = 60006.47000 (Hz) Natural freq (Mode 760) = 60127.36000 (Hz) Natural freq (Mode 761) = 60224.49000 (Hz) Natural freq (Mode 762) = 60294.48000 (Hz) Natural freq (Mode 763) = 60324.69000 (Hz) Natural freq (Mode 764) = 60396.43000 (Hz) Natural freq (Mode 765) = 60515.33000 (Hz) Natural freq (Mode 766) = 60559.32000 (Hz) Natural freq (Mode 767) = 60678.05000 (Hz) Natural freq (Mode 768) = 60828.19000 (Hz) Natural freq (Mode 769) = 60907.92000 (Hz) Natural freq (Mode 770) = 61254.36000 (Hz) Natural freq (Mode 771) = 61307.17000 (Hz) Natural freq (Mode 772) = 61381.37000 (Hz) Natural freq (Mode 773) = 61481.29000 (Hz) Natural freq (Mode 774) = 61562.68000 (Hz) Natural freq (Mode 775) = 61716.24000 (Hz) Natural freq (Mode 776) = 61781.28000 (Hz) Natural freq (Mode 777) = 61795.57000 (Hz) Natural freq (Mode 778) = 61994.89000 (Hz) Natural freq (Mode 779) = 62094.15000 (Hz) Natural freq (Mode 780) = 62113.02000 (Hz) Natural freq (Mode 781) = 62222.04000 (Hz) Natural freq (Mode 782) = 62288.52000 (Hz) Natural freq (Mode 783) = 62385.94000 (Hz) Natural freq (Mode 784) = 62396.24000 (Hz) Natural freq (Mode 785) = 62527.74000 (Hz) Natural freq (Mode 786) = 62579.81000 (Hz) Natural freq (Mode 787) = 62721.25000 (Hz) Natural freq (Mode 788) = 62738.94000 (Hz) Natural freq (Mode 789) = 62865.63000 (Hz) Natural freq (Mode 790) = 62948.16000 (Hz) Natural freq (Mode 791) = 63042.76000 (Hz) Natural freq (Mode 792) = 63143.53000 (Hz) Natural freq (Mode 793) = 63170.49000 (Hz) Natural freq (Mode 794) = 63233.18000 (Hz) Natural freq (Mode 795) = 63391.41000 (Hz) Natural freq (Mode 796) = 63540.32000 (Hz) Natural freq (Mode 797) = 63602.34000 (Hz) Natural freq (Mode 798) = 63750.55000 (Hz) Natural freq (Mode 799) = 63885.63000 (Hz) Natural freq (Mode 800) = 63965.49000 (Hz) Natural freq (Mode 801) = 64042.26000 (Hz) Natural freq (Mode 802) = 64146.40000 (Hz) Natural freq (Mode 803) = 64163.32000 (Hz) Natural freq (Mode 804) = 64321.53000 (Hz) Natural freq (Mode 805) = 64416.47000 (Hz) Natural freq (Mode 806) = 64596.16000 (Hz) Natural freq (Mode 807) = 64668.98000 (Hz) Natural freq (Mode 808) = 64816.43000 (Hz) Natural freq (Mode 809) = 64962.29000 (Hz) Natural freq (Mode 810) = 65109.30000 (Hz) Natural freq (Mode 811) = 65160.50000 (Hz) Natural freq (Mode 812) = 65187.46000 (Hz) Natural freq (Mode 813) = 65332.37000 (Hz) Natural freq (Mode 814) = 65388.61000 (Hz) Natural freq (Mode 815) = 65410.63000 (Hz) Natural freq (Mode 816) = 65475.19000 (Hz) Natural freq (Mode 817) = 65597.51000 (Hz) Natural freq (Mode 818) = 65661.34000 (Hz) Natural freq (Mode 819) = 65720.16000 (Hz) Natural freq (Mode 820) = 65867.98000 (Hz) Natural freq (Mode 821) = 66059.62000 (Hz) Natural freq (Mode 822) = 66131.58000 (Hz) Natural freq (Mode 823) = 66322.35000 (Hz) Natural freq (Mode 824) = 66464.03000 (Hz) Natural freq (Mode 825) = 66530.87000 (Hz) Natural freq (Mode 826) = 66564.12000 (Hz) Natural freq (Mode 827) = 66605.34000 (Hz) Natural freq (Mode 828) = 66789.47000 (Hz) Natural freq (Mode 829) = 66945.90000 (Hz) Natural freq (Mode 830) = 66998.07000 (Hz) Natural freq (Mode 831) = 67080.26000 (Hz) Natural freq (Mode 832) = 67189.01000 (Hz) Natural freq (Mode 833) = 67243.66000 (Hz) Natural freq (Mode 834) = 67296.74000 (Hz) Natural freq (Mode 835) = 67376.41000 (Hz) Natural freq (Mode 836) = 67513.82000 (Hz) Natural freq (Mode 837) = 67567.81000 (Hz) Natural freq (Mode 838) = 67666.32000 (Hz) Natural freq (Mode 839) = 67841.24000 (Hz) Natural freq (Mode 840) = 67908.45000 (Hz) Natural freq (Mode 841) = 68016.58000 (Hz) Natural freq (Mode 842) = 68079.98000 (Hz) Natural freq (Mode 843) = 68176.81000 (Hz) Natural freq (Mode 844) = 68460.19000 (Hz) Natural freq (Mode 845) = 68554.47000 (Hz) Natural freq (Mode 846) = 68590.22000 (Hz) Natural freq (Mode 847) = 68651.88000 (Hz) Natural freq (Mode 848) = 68687.21000 (Hz) Natural freq (Mode 849) = 68786.12000 (Hz) Natural freq (Mode 850) = 68856.07000 (Hz) Natural freq (Mode 851) = 68911.45000 (Hz) Natural freq (Mode 852) = 68921.30000 (Hz) Natural freq (Mode 853) = 69021.59000 (Hz) Natural freq (Mode 854) = 69065.40000 (Hz) Natural freq (Mode 855) = 69205.85000 (Hz) Natural freq (Mode 856) = 69252.89000 (Hz) Natural freq (Mode 857) = 69340.47000 (Hz) Natural freq (Mode 858) = 69375.84000 (Hz) Natural freq (Mode 859) = 69440.12000 (Hz) Natural freq (Mode 860) = 69512.06000 (Hz) Natural freq (Mode 861) = 69654.96000 (Hz) Natural freq (Mode 862) = 69777.94000 (Hz) Natural freq (Mode 863) = 69802.79000 (Hz) Natural freq (Mode 864) = 69841.16000 (Hz) Natural freq (Mode 865) = 69862.84000 (Hz) Natural freq (Mode 866) = 70097.50000 (Hz) Natural freq (Mode 867) = 70162.36000 (Hz) Natural freq (Mode 868) = 70263.24000 (Hz) Natural freq (Mode 869) = 70382.94000 (Hz) Natural freq (Mode 870) = 70458.26000 (Hz) Natural freq (Mode 871) = 70518.42000 (Hz) Natural freq (Mode 872) = 70586.77000 (Hz) Natural freq (Mode 873) = 70696.01000 (Hz) Natural freq (Mode 874) = 70815.79000 (Hz) Natural freq (Mode 875) = 70909.97000 (Hz) Natural freq (Mode 876) = 70983.21000 (Hz) Natural freq (Mode 877) = 71056.86000 (Hz) Natural freq (Mode 878) = 71154.90000 (Hz) Natural freq (Mode 879) = 71186.77000 (Hz) Natural freq (Mode 880) = 71297.27000 (Hz) Natural freq (Mode 881) = 71311.62000 (Hz) Natural freq (Mode 882) = 71367.08000 (Hz) Natural freq (Mode 883) = 71546.12000 (Hz) Natural freq (Mode 884) = 71616.69000 (Hz) Natural freq (Mode 885) = 71716.84000 (Hz) Natural freq (Mode 886) = 71918.26000 (Hz) Natural freq (Mode 887) = 72018.71000 (Hz) Natural freq (Mode 888) = 72140.89000 (Hz) Natural freq (Mode 889) = 72189.70000 (Hz) Natural freq (Mode 890) = 72303.92000 (Hz) Natural freq (Mode 891) = 72392.19000 (Hz) Natural freq (Mode 892) = 72479.59000 (Hz) Natural freq (Mode 893) = 72685.64000 (Hz) Natural freq (Mode 894) = 72758.08000 (Hz) Natural freq (Mode 895) = 72772.19000 (Hz) Natural freq (Mode 896) = 72899.19000 (Hz) Natural freq (Mode 897) = 73060.15000 (Hz) Natural freq (Mode 898) = 73133.38000 (Hz) Natural freq (Mode 899) = 73302.51000 (Hz) Natural freq (Mode 900) = 73340.19000 (Hz) Natural freq (Mode 901) = 73393.19000 (Hz) Natural freq (Mode 902) = 73522.47000 (Hz) Natural freq (Mode 903) = 73626.04000 (Hz) Natural freq (Mode 904) = 73721.49000 (Hz) Natural freq (Mode 905) = 73739.77000 (Hz) Natural freq (Mode 906) = 73766.51000 (Hz) Natural freq (Mode 907) = 73944.32000 (Hz) Natural freq (Mode 908) = 74006.82000 (Hz) Natural freq (Mode 909) = 74121.25000 (Hz) Natural freq (Mode 910) = 74153.07000 (Hz) Natural freq (Mode 911) = 74175.30000 (Hz) Natural freq (Mode 912) = 74249.00000 (Hz) Natural freq (Mode 913) = 74364.63000 (Hz) Natural freq (Mode 914) = 74494.14000 (Hz) Natural freq (Mode 915) = 74538.38000 (Hz) Natural freq (Mode 916) = 74634.16000 (Hz) Natural freq (Mode 917) = 74679.94000 (Hz) Natural freq (Mode 918) = 74739.85000 (Hz) Natural freq (Mode 919) = 74803.58000 (Hz) Natural freq (Mode 920) = 74993.28000 (Hz) Natural freq (Mode 921) = 75053.98000 (Hz) Natural freq (Mode 922) = 75093.93000 (Hz) Natural freq (Mode 923) = 75299.71000 (Hz) Natural freq (Mode 924) = 75358.80000 (Hz) Natural freq (Mode 925) = 75425.58000 (Hz) Natural freq (Mode 926) = 75536.12000 (Hz) Natural freq (Mode 927) = 75713.14000 (Hz) Natural freq (Mode 928) = 75834.39000 (Hz) Natural freq (Mode 929) = 75884.56000 (Hz) Natural freq (Mode 930) = 76007.14000 (Hz) Natural freq (Mode 931) = 76120.42000 (Hz) Natural freq (Mode 932) = 76225.74000 (Hz) Natural freq (Mode 933) = 76255.57000 (Hz) Natural freq (Mode 934) = 76430.79000 (Hz) Natural freq (Mode 935) = 76638.92000 (Hz) Natural freq (Mode 936) = 76687.01000 (Hz) Natural freq (Mode 937) = 76810.80000 (Hz) Natural freq (Mode 938) = 76828.09000 (Hz) Natural freq (Mode 939) = 76925.01000 (Hz) Natural freq (Mode 940) = 77008.94000 (Hz) Natural freq (Mode 941) = 77102.92000 (Hz) Natural freq (Mode 942) = 77151.28000 (Hz) Natural freq (Mode 943) = 77289.38000 (Hz) Natural freq (Mode 944) = 77372.04000 (Hz) Natural freq (Mode 945) = 77376.51000 (Hz) Natural freq (Mode 946) = 77440.76000 (Hz) Natural freq (Mode 947) = 77523.43000 (Hz) Natural freq (Mode 948) = 77561.89000 (Hz) Natural freq (Mode 949) = 77587.38000 (Hz) Natural freq (Mode 950) = 77748.95000 (Hz) Natural freq (Mode 951) = 77853.38000 (Hz) Natural freq (Mode 952) = 77858.82000 (Hz) Natural freq (Mode 953) = 77953.25000 (Hz) Natural freq (Mode 954) = 78000.41000 (Hz) Natural freq (Mode 955) = 78099.35000 (Hz) Natural freq (Mode 956) = 78253.68000 (Hz) Natural freq (Mode 957) = 78382.22000 (Hz) Natural freq (Mode 958) = 78418.48000 (Hz) Natural freq (Mode 959) = 78515.48000 (Hz) Natural freq (Mode 960) = 78610.92000 (Hz) Natural freq (Mode 961) = 78645.10000 (Hz) Natural freq (Mode 962) = 78727.57000 (Hz) Natural freq (Mode 963) = 78863.91000 (Hz) Natural freq (Mode 964) = 78937.32000 (Hz) Natural freq (Mode 965) = 79053.58000 (Hz) Natural freq (Mode 966) = 79077.26000 (Hz) Natural freq (Mode 967) = 79215.24000 (Hz) Natural freq (Mode 968) = 79294.12000 (Hz) Natural freq (Mode 969) = 79324.82000 (Hz) Natural freq (Mode 970) = 79362.91000 (Hz) Natural freq (Mode 971) = 79527.23000 (Hz) Natural freq (Mode 972) = 79611.69000 (Hz) Natural freq (Mode 973) = 79647.10000 (Hz) Natural freq (Mode 974) = 79832.89000 (Hz) Natural freq (Mode 975) = 79866.64000 (Hz) Natural freq (Mode 976) = 79970.43000 (Hz) Natural freq (Mode 977) = 80030.32000 (Hz) Natural freq (Mode 978) = 80104.74000 (Hz) Natural freq (Mode 979) = 80123.64000 (Hz) Natural freq (Mode 980) = 80182.67000 (Hz) Natural freq (Mode 981) = 80321.53000 (Hz) Natural freq (Mode 982) = 80385.61000 (Hz) Natural freq (Mode 983) = 80444.38000 (Hz) Natural freq (Mode 984) = 80581.53000 (Hz) Natural freq (Mode 985) = 80665.28000 (Hz) Natural freq (Mode 986) = 80757.29000 (Hz) Natural freq (Mode 987) = 80846.96000 (Hz) Natural freq (Mode 988) = 81004.13000 (Hz) Natural freq (Mode 989) = 81044.79000 (Hz) Natural freq (Mode 990) = 81140.53000 (Hz) Natural freq (Mode 991) = 81244.66000 (Hz) Natural freq (Mode 992) = 81434.94000 (Hz) Natural freq (Mode 993) = 81460.92000 (Hz) Natural freq (Mode 994) = 81502.50000 (Hz) Natural freq (Mode 995) = 81572.23000 (Hz) Natural freq (Mode 996) = 81703.12000 (Hz) Natural freq (Mode 997) = 81809.87000 (Hz) Natural freq (Mode 998) = 81917.77000 (Hz) Natural freq (Mode 999) = 81922.97000 (Hz) Natural freq (Mode 1000) = 82100.35000 (Hz) Natural freq (Mode 1001) = 82120.03000 (Hz) Natural freq (Mode 1002) = 82160.63000 (Hz) Natural freq (Mode 1003) = 82272.67000 (Hz) Natural freq (Mode 1004) = 82375.92000 (Hz) Natural freq (Mode 1005) = 82426.08000 (Hz) Natural freq (Mode 1006) = 82607.53000 (Hz) Natural freq (Mode 1007) = 82667.54000 (Hz) Natural freq (Mode 1008) = 82795.73000 (Hz) Natural freq (Mode 1009) = 82830.25000 (Hz) Natural freq (Mode 1010) = 82913.56000 (Hz) Natural freq (Mode 1011) = 83117.39000 (Hz) Natural freq (Mode 1012) = 83264.48000 (Hz) Natural freq (Mode 1013) = 83303.87000 (Hz) Natural freq (Mode 1014) = 83383.77000 (Hz) Natural freq (Mode 1015) = 83474.57000 (Hz) Natural freq (Mode 1016) = 83564.55000 (Hz) Natural freq (Mode 1017) = 83612.36000 (Hz) Natural freq (Mode 1018) = 83635.59000 (Hz) Natural freq (Mode 1019) = 83660.44000 (Hz) Natural freq (Mode 1020) = 83784.58000 (Hz) Natural freq (Mode 1021) = 83861.33000 (Hz) Natural freq (Mode 1022) = 83937.67000 (Hz) Natural freq (Mode 1023) = 84023.90000 (Hz) Natural freq (Mode 1024) = 84139.57000 (Hz) Natural freq (Mode 1025) = 84188.86000 (Hz) Natural freq (Mode 1026) = 84266.69000 (Hz) Natural freq (Mode 1027) = 84269.75000 (Hz) Natural freq (Mode 1028) = 84309.34000 (Hz) Natural freq (Mode 1029) = 84427.03000 (Hz) Natural freq (Mode 1030) = 84673.20000 (Hz) Natural freq (Mode 1031) = 84725.60000 (Hz) Natural freq (Mode 1032) = 84802.77000 (Hz) Natural freq (Mode 1033) = 84921.77000 (Hz) Natural freq (Mode 1034) = 84960.34000 (Hz) Natural freq (Mode 1035) = 85091.32000 (Hz) Natural freq (Mode 1036) = 85116.43000 (Hz) Natural freq (Mode 1037) = 85264.96000 (Hz) Natural freq (Mode 1038) = 85286.54000 (Hz) Natural freq (Mode 1039) = 85306.32000 (Hz) Natural freq (Mode 1040) = 85421.91000 (Hz) Natural freq (Mode 1041) = 85547.09000 (Hz) Natural freq (Mode 1042) = 85661.92000 (Hz) Natural freq (Mode 1043) = 85719.86000 (Hz) Natural freq (Mode 1044) = 85749.15000 (Hz) Natural freq (Mode 1045) = 85924.99000 (Hz) Natural freq (Mode 1046) = 86089.57000 (Hz) Natural freq (Mode 1047) = 86148.53000 (Hz) Natural freq (Mode 1048) = 86302.17000 (Hz) Natural freq (Mode 1049) = 86373.30000 (Hz) Natural freq (Mode 1050) = 86491.27000 (Hz) Natural freq (Mode 1051) = 86624.46000 (Hz) Natural freq (Mode 1052) = 86658.50000 (Hz) Natural freq (Mode 1053) = 86688.69000 (Hz) Natural freq (Mode 1054) = 86846.44000 (Hz) Natural freq (Mode 1055) = 86952.64000 (Hz) Natural freq (Mode 1056) = 87074.96000 (Hz) Natural freq (Mode 1057) = 87237.35000 (Hz) Natural freq (Mode 1058) = 87398.33000 (Hz) Natural freq (Mode 1059) = 87464.73000 (Hz) Natural freq (Mode 1060) = 87561.27000 (Hz) Natural freq (Mode 1061) = 87628.88000 (Hz) Natural freq (Mode 1062) = 87672.54000 (Hz) Natural freq (Mode 1063) = 87868.90000 (Hz) Natural freq (Mode 1064) = 87909.61000 (Hz) Natural freq (Mode 1065) = 87948.39000 (Hz) Natural freq (Mode 1066) = 88031.61000 (Hz) Natural freq (Mode 1067) = 88056.46000 (Hz) Natural freq (Mode 1068) = 88172.09000 (Hz) Natural freq (Mode 1069) = 88206.87000 (Hz) Natural freq (Mode 1070) = 88308.04000 (Hz) Natural freq (Mode 1071) = 88352.02000 (Hz) Natural freq (Mode 1072) = 88465.10000 (Hz) Natural freq (Mode 1073) = 88565.23000 (Hz) Natural freq (Mode 1074) = 88657.34000 (Hz) Natural freq (Mode 1075) = 88700.26000 (Hz) Natural freq (Mode 1076) = 88709.47000 (Hz) Natural freq (Mode 1077) = 88724.85000 (Hz) Natural freq (Mode 1078) = 88816.78000 (Hz) Natural freq (Mode 1079) = 88873.34000 (Hz) Natural freq (Mode 1080) = 89020.17000 (Hz) Natural freq (Mode 1081) = 89078.82000 (Hz) Natural freq (Mode 1082) = 89146.32000 (Hz) Natural freq (Mode 1083) = 89216.51000 (Hz) Natural freq (Mode 1084) = 89285.04000 (Hz) Natural freq (Mode 1085) = 89306.96000 (Hz) Natural freq (Mode 1086) = 89439.18000 (Hz) Natural freq (Mode 1087) = 89528.18000 (Hz) Natural freq (Mode 1088) = 89620.32000 (Hz) Natural freq (Mode 1089) = 89716.06000 (Hz) Natural freq (Mode 1090) = 89813.61000 (Hz) Natural freq (Mode 1091) = 89915.21000 (Hz) Natural freq (Mode 1092) = 89957.09000 (Hz) Natural freq (Mode 1093) = 90076.36000 (Hz) Natural freq (Mode 1094) = 90217.64000 (Hz) Natural freq (Mode 1095) = 90281.78000 (Hz) Natural freq (Mode 1096) = 90337.50000 (Hz) Natural freq (Mode 1097) = 90383.03000 (Hz) Natural freq (Mode 1098) = 90467.45000 (Hz) Natural freq (Mode 1099) = 90504.77000 (Hz) Natural freq (Mode 1100) = 90625.35000 (Hz) Natural freq (Mode 1101) = 90713.12000 (Hz) Natural freq (Mode 1102) = 90740.85000 (Hz) Natural freq (Mode 1103) = 90752.30000 (Hz) Natural freq (Mode 1104) = 90845.66000 (Hz) Natural freq (Mode 1105) = 90901.66000 (Hz) Natural freq (Mode 1106) = 91071.76000 (Hz) Natural freq (Mode 1107) = 91110.43000 (Hz) Natural freq (Mode 1108) = 91256.23000 (Hz) Natural freq (Mode 1109) = 91418.58000 (Hz) Natural freq (Mode 1110) = 91547.07000 (Hz) Natural freq (Mode 1111) = 91607.19000 (Hz) Natural freq (Mode 1112) = 91650.98000 (Hz) Natural freq (Mode 1113) = 91713.15000 (Hz) Natural freq (Mode 1114) = 91833.30000 (Hz) Natural freq (Mode 1115) = 91977.28000 (Hz) Natural freq (Mode 1116) = 92097.01000 (Hz) Natural freq (Mode 1117) = 92197.90000 (Hz) Natural freq (Mode 1118) = 92227.72000 (Hz) Natural freq (Mode 1119) = 92254.49000 (Hz) Natural freq (Mode 1120) = 92434.76000 (Hz) Natural freq (Mode 1121) = 92530.93000 (Hz) Natural freq (Mode 1122) = 92547.32000 (Hz) Natural freq (Mode 1123) = 92617.38000 (Hz) Natural freq (Mode 1124) = 92860.10000 (Hz) Natural freq (Mode 1125) = 92989.60000 (Hz) Natural freq (Mode 1126) = 93070.57000 (Hz) Natural freq (Mode 1127) = 93135.01000 (Hz) Natural freq (Mode 1128) = 93268.29000 (Hz) Natural freq (Mode 1129) = 93358.34000 (Hz) Natural freq (Mode 1130) = 93369.00000 (Hz) Natural freq (Mode 1131) = 93384.06000 (Hz) Natural freq (Mode 1132) = 93491.51000 (Hz) Natural freq (Mode 1133) = 93537.09000 (Hz) Natural freq (Mode 1134) = 93562.33000 (Hz) Natural freq (Mode 1135) = 93754.73000 (Hz) Natural freq (Mode 1136) = 93814.21000 (Hz) Natural freq (Mode 1137) = 93871.80000 (Hz) Natural freq (Mode 1138) = 93938.57000 (Hz) Natural freq (Mode 1139) = 94024.20000 (Hz) Natural freq (Mode 1140) = 94128.21000 (Hz) Natural freq (Mode 1141) = 94232.26000 (Hz) Natural freq (Mode 1142) = 94351.51000 (Hz) Natural freq (Mode 1143) = 94409.17000 (Hz) Natural freq (Mode 1144) = 94558.20000 (Hz) Natural freq (Mode 1145) = 94631.15000 (Hz) Natural freq (Mode 1146) = 94732.62000 (Hz) Natural freq (Mode 1147) = 94826.06000 (Hz) Natural freq (Mode 1148) = 94976.99000 (Hz) Natural freq (Mode 1149) = 95048.56000 (Hz) Natural freq (Mode 1150) = 95181.86000 (Hz) Natural freq (Mode 1151) = 95192.30000 (Hz) Natural freq (Mode 1152) = 95297.16000 (Hz) Natural freq (Mode 1153) = 95436.33000 (Hz) Natural freq (Mode 1154) = 95618.01000 (Hz) Natural freq (Mode 1155) = 95702.23000 (Hz) Natural freq (Mode 1156) = 95750.83000 (Hz) Natural freq (Mode 1157) = 95867.23000 (Hz) Natural freq (Mode 1158) = 95962.79000 (Hz) Natural freq (Mode 1159) = 96041.91000 (Hz) Natural freq (Mode 1160) = 96091.17000 (Hz) Natural freq (Mode 1161) = 96284.30000 (Hz) Natural freq (Mode 1162) = 96348.77000 (Hz) Natural freq (Mode 1163) = 96411.30000 (Hz) Natural freq (Mode 1164) = 96457.12000 (Hz) Natural freq (Mode 1165) = 96570.81000 (Hz) Natural freq (Mode 1166) = 96623.90000 (Hz) Natural freq (Mode 1167) = 96696.38000 (Hz) Natural freq (Mode 1168) = 96737.32000 (Hz) Natural freq (Mode 1169) = 96846.65000 (Hz) Natural freq (Mode 1170) = 97008.36000 (Hz) Natural freq (Mode 1171) = 97119.42000 (Hz) Natural freq (Mode 1172) = 97233.69000 (Hz) Natural freq (Mode 1173) = 97270.07000 (Hz) Natural freq (Mode 1174) = 97447.92000 (Hz) Natural freq (Mode 1175) = 97506.07000 (Hz) Natural freq (Mode 1176) = 97594.28000 (Hz) Natural freq (Mode 1177) = 97805.04000 (Hz) Natural freq (Mode 1178) = 97894.72000 (Hz) Natural freq (Mode 1179) = 97928.87000 (Hz) Natural freq (Mode 1180) = 97981.40000 (Hz) Natural freq (Mode 1181) = 98086.96000 (Hz) Natural freq (Mode 1182) = 98117.62000 (Hz) Natural freq (Mode 1183) = 98245.71000 (Hz) Natural freq (Mode 1184) = 98360.74000 (Hz) Natural freq (Mode 1185) = 98519.72000 (Hz) Natural freq (Mode 1186) = 98691.42000 (Hz) Natural freq (Mode 1187) = 98754.68000 (Hz) Natural freq (Mode 1188) = 98877.99000 (Hz) Natural freq (Mode 1189) = 98986.09000 (Hz) Natural freq (Mode 1190) = 99067.69000 (Hz) Natural freq (Mode 1191) = 99222.21000 (Hz) Natural freq (Mode 1192) = 99324.10000 (Hz) Natural freq (Mode 1193) = 99363.49000 (Hz) Natural freq (Mode 1194) = 99552.85000 (Hz) Natural freq (Mode 1195) = 99565.86000 (Hz) Natural freq (Mode 1196) = 99651.71000 (Hz) Natural freq (Mode 1197) = 99914.16000 (Hz) Natural freq (Mode 1198) = 99997.05000 (Hz) Natural freq (Mode 1199) = 100086.10000 (Hz) Natural freq (Mode 1200) = 100112.50000 (Hz) Natural freq (Mode 1201) = 100320.50000 (Hz) Natural freq (Mode 1202) = 100334.10000 (Hz) Natural freq (Mode 1203) = 100410.10000 (Hz) Natural freq (Mode 1204) = 100520.60000 (Hz) Natural freq (Mode 1205) = 100611.10000 (Hz) Natural freq (Mode 1206) = 100756.50000 (Hz) Natural freq (Mode 1207) = 100857.90000 (Hz) Natural freq (Mode 1208) = 100906.60000 (Hz) Natural freq (Mode 1209) = 101024.70000 (Hz) Natural freq (Mode 1210) = 101217.30000 (Hz) Natural freq (Mode 1211) = 101378.20000 (Hz) Natural freq (Mode 1212) = 101425.90000 (Hz) Natural freq (Mode 1213) = 101568.40000 (Hz) Natural freq (Mode 1214) = 101649.20000 (Hz) Natural freq (Mode 1215) = 101854.50000 (Hz) Natural freq (Mode 1216) = 101859.60000 (Hz) Natural freq (Mode 1217) = 102032.30000 (Hz) Natural freq (Mode 1218) = 102118.70000 (Hz) Natural freq (Mode 1219) = 102163.20000 (Hz) Natural freq (Mode 1220) = 102309.80000 (Hz) Natural freq (Mode 1221) = 102376.90000 (Hz) Natural freq (Mode 1222) = 102475.10000 (Hz) Natural freq (Mode 1223) = 102587.10000 (Hz) Natural freq (Mode 1224) = 102626.40000 (Hz) Natural freq (Mode 1225) = 102808.10000 (Hz) Natural freq (Mode 1226) = 102999.10000 (Hz) Natural freq (Mode 1227) = 103055.40000 (Hz) Natural freq (Mode 1228) = 103153.30000 (Hz) Natural freq (Mode 1229) = 103210.50000 (Hz) Natural freq (Mode 1230) = 103389.80000 (Hz) Natural freq (Mode 1231) = 103567.90000 (Hz) Natural freq (Mode 1232) = 103741.10000 (Hz) Natural freq (Mode 1233) = 103800.40000 (Hz) Natural freq (Mode 1234) = 103844.10000 (Hz) Natural freq (Mode 1235) = 103957.40000 (Hz) Natural freq (Mode 1236) = 104142.80000 (Hz) Natural freq (Mode 1237) = 104186.80000 (Hz) Natural freq (Mode 1238) = 104368.90000 (Hz) Natural freq (Mode 1239) = 104521.90000 (Hz) Natural freq (Mode 1240) = 104605.60000 (Hz) Natural freq (Mode 1241) = 104640.40000 (Hz) Natural freq (Mode 1242) = 104752.90000 (Hz) Natural freq (Mode 1243) = 104877.60000 (Hz) Natural freq (Mode 1244) = 104974.20000 (Hz) Natural freq (Mode 1245) = 105069.10000 (Hz) Natural freq (Mode 1246) = 105261.70000 (Hz) Natural freq (Mode 1247) = 105316.40000 (Hz) Natural freq (Mode 1248) = 105535.40000 (Hz) Natural freq (Mode 1249) = 105616.20000 (Hz) Natural freq (Mode 1250) = 105792.20000 (Hz) Natural freq (Mode 1251) = 105817.40000 (Hz) Natural freq (Mode 1252) = 105974.60000 (Hz) Natural freq (Mode 1253) = 106104.30000 (Hz) Natural freq (Mode 1254) = 106143.00000 (Hz) Natural freq (Mode 1255) = 106291.00000 (Hz) Natural freq (Mode 1256) = 106393.00000 (Hz) Natural freq (Mode 1257) = 106517.20000 (Hz) Natural freq (Mode 1258) = 106601.60000 (Hz) Natural freq (Mode 1259) = 106776.20000 (Hz) Natural freq (Mode 1260) = 106847.60000 (Hz) Natural freq (Mode 1261) = 106928.10000 (Hz) Natural freq (Mode 1262) = 107010.40000 (Hz) Natural freq (Mode 1263) = 107146.40000 (Hz) Natural freq (Mode 1264) = 107311.10000 (Hz) Natural freq (Mode 1265) = 107361.80000 (Hz) Natural freq (Mode 1266) = 107415.20000 (Hz) Natural freq (Mode 1267) = 107609.10000 (Hz) Natural freq (Mode 1268) = 107719.30000 (Hz) Natural freq (Mode 1269) = 108001.00000 (Hz) Natural freq (Mode 1270) = 108061.80000 (Hz) Natural freq (Mode 1271) = 108076.50000 (Hz) Natural freq (Mode 1272) = 108252.70000 (Hz) Natural freq (Mode 1273) = 108325.20000 (Hz) Natural freq (Mode 1274) = 108375.60000 (Hz) Natural freq (Mode 1275) = 108506.50000 (Hz) Natural freq (Mode 1276) = 108549.10000 (Hz) Natural freq (Mode 1277) = 108709.70000 (Hz) Natural freq (Mode 1278) = 108776.70000 (Hz) Natural freq (Mode 1279) = 108840.10000 (Hz) Natural freq (Mode 1280) = 109176.60000 (Hz) Natural freq (Mode 1281) = 109253.60000 (Hz) Natural freq (Mode 1282) = 109305.80000 (Hz) Natural freq (Mode 1283) = 109383.00000 (Hz) Natural freq (Mode 1284) = 109470.60000 (Hz) Natural freq (Mode 1285) = 109580.90000 (Hz) Natural freq (Mode 1286) = 109637.50000 (Hz) Natural freq (Mode 1287) = 109903.10000 (Hz) Natural freq (Mode 1288) = 109941.40000 (Hz) Natural freq (Mode 1289) = 109970.10000 (Hz) Natural freq (Mode 1290) = 110176.20000 (Hz) Natural freq (Mode 1291) = 110262.20000 (Hz) Natural freq (Mode 1292) = 110397.60000 (Hz) Natural freq (Mode 1293) = 110469.50000 (Hz) Natural freq (Mode 1294) = 110498.80000 (Hz) Natural freq (Mode 1295) = 110660.80000 (Hz) Natural freq (Mode 1296) = 110709.90000 (Hz) Natural freq (Mode 1297) = 110855.40000 (Hz) Natural freq (Mode 1298) = 111003.50000 (Hz) Natural freq (Mode 1299) = 111108.40000 (Hz) Natural freq (Mode 1300) = 111239.20000 (Hz) Natural freq (Mode 1301) = 111263.50000 (Hz) Natural freq (Mode 1302) = 111446.80000 (Hz) Natural freq (Mode 1303) = 111644.50000 (Hz) Natural freq (Mode 1304) = 111765.20000 (Hz) Natural freq (Mode 1305) = 111843.10000 (Hz) Natural freq (Mode 1306) = 111987.60000 (Hz) Natural freq (Mode 1307) = 112035.40000 (Hz) Natural freq (Mode 1308) = 112128.30000 (Hz) Natural freq (Mode 1309) = 112392.30000 (Hz) Natural freq (Mode 1310) = 112433.70000 (Hz) Natural freq (Mode 1311) = 112461.80000 (Hz) Natural freq (Mode 1312) = 112598.60000 (Hz) Natural freq (Mode 1313) = 112674.70000 (Hz) Natural freq (Mode 1314) = 112785.90000 (Hz) Natural freq (Mode 1315) = 112877.40000 (Hz) Natural freq (Mode 1316) = 112951.70000 (Hz) Natural freq (Mode 1317) = 113078.10000 (Hz) Natural freq (Mode 1318) = 113182.60000 (Hz) Natural freq (Mode 1319) = 113251.80000 (Hz) Natural freq (Mode 1320) = 113572.60000 (Hz) Natural freq (Mode 1321) = 113614.80000 (Hz) Natural freq (Mode 1322) = 113655.60000 (Hz) Natural freq (Mode 1323) = 114032.30000 (Hz) Natural freq (Mode 1324) = 114186.80000 (Hz) Natural freq (Mode 1325) = 114294.00000 (Hz) Natural freq (Mode 1326) = 114354.20000 (Hz) Natural freq (Mode 1327) = 114521.20000 (Hz) Natural freq (Mode 1328) = 114551.30000 (Hz) Natural freq (Mode 1329) = 114600.10000 (Hz) Natural freq (Mode 1330) = 114716.60000 (Hz) Natural freq (Mode 1331) = 114808.50000 (Hz) Natural freq (Mode 1332) = 114961.50000 (Hz) Natural freq (Mode 1333) = 115052.60000 (Hz) Natural freq (Mode 1334) = 115156.20000 (Hz) Natural freq (Mode 1335) = 115377.20000 (Hz) Natural freq (Mode 1336) = 115484.80000 (Hz) Natural freq (Mode 1337) = 115597.90000 (Hz) Natural freq (Mode 1338) = 115718.90000 (Hz) Natural freq (Mode 1339) = 115960.20000 (Hz) Natural freq (Mode 1340) = 116114.10000 (Hz) Natural freq (Mode 1341) = 116243.00000 (Hz) Natural freq (Mode 1342) = 116262.40000 (Hz) Natural freq (Mode 1343) = 116413.40000 (Hz) Natural freq (Mode 1344) = 116477.70000 (Hz) Natural freq (Mode 1345) = 116555.20000 (Hz) Natural freq (Mode 1346) = 116672.70000 (Hz) Natural freq (Mode 1347) = 116713.00000 (Hz) Natural freq (Mode 1348) = 116874.30000 (Hz) Natural freq (Mode 1349) = 117031.80000 (Hz) Natural freq (Mode 1350) = 117183.70000 (Hz) Natural freq (Mode 1351) = 117264.80000 (Hz) Natural freq (Mode 1352) = 117412.80000 (Hz) Natural freq (Mode 1353) = 117527.50000 (Hz) Natural freq (Mode 1354) = 117697.90000 (Hz) Natural freq (Mode 1355) = 117771.70000 (Hz) Natural freq (Mode 1356) = 117868.10000 (Hz) Natural freq (Mode 1357) = 117969.50000 (Hz) Natural freq (Mode 1358) = 118129.50000 (Hz) Natural freq (Mode 1359) = 118302.40000 (Hz) Natural freq (Mode 1360) = 118370.90000 (Hz) Natural freq (Mode 1361) = 118419.00000 (Hz) Natural freq (Mode 1362) = 118571.50000 (Hz) Natural freq (Mode 1363) = 118877.20000 (Hz) Natural freq (Mode 1364) = 118947.70000 (Hz) Natural freq (Mode 1365) = 118997.70000 (Hz) Natural freq (Mode 1366) = 119126.20000 (Hz) Natural freq (Mode 1367) = 119270.50000 (Hz) Natural freq (Mode 1368) = 119406.20000 (Hz) Natural freq (Mode 1369) = 119511.30000 (Hz) Natural freq (Mode 1370) = 119574.30000 (Hz) Natural freq (Mode 1371) = 119781.00000 (Hz) Natural freq (Mode 1372) = 119933.60000 (Hz) Natural freq (Mode 1373) = 120145.60000 (Hz) Natural freq (Mode 1374) = 120190.00000 (Hz) Natural freq (Mode 1375) = 120321.80000 (Hz) Natural freq (Mode 1376) = 120353.10000 (Hz) Natural freq (Mode 1377) = 120597.80000 (Hz) Natural freq (Mode 1378) = 120644.50000 (Hz) Natural freq (Mode 1379) = 120725.60000 (Hz) Natural freq (Mode 1380) = 120837.90000 (Hz) Natural freq (Mode 1381) = 120870.10000 (Hz) Natural freq (Mode 1382) = 121080.50000 (Hz) Natural freq (Mode 1383) = 121177.30000 (Hz) Natural freq (Mode 1384) = 121278.30000 (Hz) Natural freq (Mode 1385) = 121504.70000 (Hz) Natural freq (Mode 1386) = 121567.70000 (Hz) Natural freq (Mode 1387) = 121628.50000 (Hz) Natural freq (Mode 1388) = 121743.40000 (Hz) Natural freq (Mode 1389) = 121787.00000 (Hz) Natural freq (Mode 1390) = 122020.70000 (Hz) Natural freq (Mode 1391) = 122085.30000 (Hz) Natural freq (Mode 1392) = 122227.70000 (Hz) Natural freq (Mode 1393) = 122430.00000 (Hz) Natural freq (Mode 1394) = 122517.90000 (Hz) Natural freq (Mode 1395) = 122566.40000 (Hz) Natural freq (Mode 1396) = 122794.80000 (Hz) Natural freq (Mode 1397) = 122905.20000 (Hz) Natural freq (Mode 1398) = 123064.90000 (Hz) Natural freq (Mode 1399) = 123171.70000 (Hz) Natural freq (Mode 1400) = 123264.40000 (Hz) Natural freq (Mode 1401) = 123359.30000 (Hz) Natural freq (Mode 1402) = 123494.90000 (Hz) Natural freq (Mode 1403) = 123758.80000 (Hz) Natural freq (Mode 1404) = 123897.70000 (Hz) Natural freq (Mode 1405) = 124106.20000 (Hz) Natural freq (Mode 1406) = 124163.70000 (Hz) Natural freq (Mode 1407) = 124297.60000 (Hz) Natural freq (Mode 1408) = 124377.30000 (Hz) Natural freq (Mode 1409) = 124544.60000 (Hz) Natural freq (Mode 1410) = 124658.30000 (Hz) Natural freq (Mode 1411) = 124674.60000 (Hz) Natural freq (Mode 1412) = 124969.70000 (Hz) Natural freq (Mode 1413) = 125010.20000 (Hz) Natural freq (Mode 1414) = 125106.50000 (Hz) Natural freq (Mode 1415) = 125287.30000 (Hz) Natural freq (Mode 1416) = 125364.30000 (Hz) Natural freq (Mode 1417) = 125496.00000 (Hz) Natural freq (Mode 1418) = 125668.20000 (Hz) Natural freq (Mode 1419) = 125806.90000 (Hz) Natural freq (Mode 1420) = 125859.20000 (Hz) Natural freq (Mode 1421) = 126124.10000 (Hz) Natural freq (Mode 1422) = 126336.10000 (Hz) Natural freq (Mode 1423) = 126512.70000 (Hz) Natural freq (Mode 1424) = 126539.10000 (Hz) Natural freq (Mode 1425) = 126620.50000 (Hz) Natural freq (Mode 1426) = 126877.60000 (Hz) Natural freq (Mode 1427) = 126962.30000 (Hz) Natural freq (Mode 1428) = 127132.20000 (Hz) Natural freq (Mode 1429) = 127254.70000 (Hz) Natural freq (Mode 1430) = 127477.10000 (Hz) Natural freq (Mode 1431) = 127659.30000 (Hz) Natural freq (Mode 1432) = 127893.90000 (Hz) Natural freq (Mode 1433) = 127957.60000 (Hz) Natural freq (Mode 1434) = 128099.20000 (Hz) Natural freq (Mode 1435) = 128180.30000 (Hz) Natural freq (Mode 1436) = 128320.40000 (Hz) Natural freq (Mode 1437) = 128363.50000 (Hz) Natural freq (Mode 1438) = 128546.60000 (Hz) Natural freq (Mode 1439) = 128764.90000 (Hz) Natural freq (Mode 1440) = 128804.00000 (Hz) Natural freq (Mode 1441) = 128925.30000 (Hz) Natural freq (Mode 1442) = 128959.00000 (Hz) Natural freq (Mode 1443) = 128969.90000 (Hz) Natural freq (Mode 1444) = 129220.00000 (Hz) Natural freq (Mode 1445) = 129323.20000 (Hz) Natural freq (Mode 1446) = 129474.70000 (Hz) Natural freq (Mode 1447) = 129675.90000 (Hz) Natural freq (Mode 1448) = 129703.10000 (Hz) Natural freq (Mode 1449) = 130113.10000 (Hz) Natural freq (Mode 1450) = 130185.80000 (Hz) Natural freq (Mode 1451) = 130348.10000 (Hz) Natural freq (Mode 1452) = 130578.30000 (Hz) Natural freq (Mode 1453) = 130708.50000 (Hz) Natural freq (Mode 1454) = 130869.20000 (Hz) Natural freq (Mode 1455) = 130922.50000 (Hz) Natural freq (Mode 1456) = 131020.90000 (Hz) Natural freq (Mode 1457) = 131122.90000 (Hz) Natural freq (Mode 1458) = 131424.50000 (Hz) Natural freq (Mode 1459) = 131584.80000 (Hz) Natural freq (Mode 1460) = 131684.30000 (Hz) Natural freq (Mode 1461) = 131809.90000 (Hz) Natural freq (Mode 1462) = 131858.60000 (Hz) Natural freq (Mode 1463) = 131958.50000 (Hz) Natural freq (Mode 1464) = 132233.70000 (Hz) Natural freq (Mode 1465) = 132449.40000 (Hz) Natural freq (Mode 1466) = 132607.40000 (Hz) Natural freq (Mode 1467) = 132729.70000 (Hz) Natural freq (Mode 1468) = 132880.40000 (Hz) Natural freq (Mode 1469) = 133046.80000 (Hz) Natural freq (Mode 1470) = 133201.30000 (Hz) Natural freq (Mode 1471) = 133234.10000 (Hz) Natural freq (Mode 1472) = 133629.50000 (Hz) Natural freq (Mode 1473) = 133796.90000 (Hz) Natural freq (Mode 1474) = 133948.40000 (Hz) Natural freq (Mode 1475) = 134006.30000 (Hz) Natural freq (Mode 1476) = 134324.40000 (Hz) Natural freq (Mode 1477) = 134507.70000 (Hz) Natural freq (Mode 1478) = 134620.10000 (Hz) Natural freq (Mode 1479) = 134837.70000 (Hz) Natural freq (Mode 1480) = 134916.50000 (Hz) Natural freq (Mode 1481) = 135097.00000 (Hz) Natural freq (Mode 1482) = 135137.40000 (Hz) Natural freq (Mode 1483) = 135476.30000 (Hz) Natural freq (Mode 1484) = 135553.40000 (Hz) Natural freq (Mode 1485) = 135680.90000 (Hz) Natural freq (Mode 1486) = 135723.70000 (Hz) Natural freq (Mode 1487) = 136137.20000 (Hz) Natural freq (Mode 1488) = 136254.00000 (Hz) Natural freq (Mode 1489) = 136531.70000 (Hz) Natural freq (Mode 1490) = 136629.60000 (Hz) Natural freq (Mode 1491) = 136739.30000 (Hz) Natural freq (Mode 1492) = 136927.00000 (Hz) Natural freq (Mode 1493) = 136989.70000 (Hz) Natural freq (Mode 1494) = 137183.70000 (Hz) Natural freq (Mode 1495) = 137230.00000 (Hz) Natural freq (Mode 1496) = 137313.30000 (Hz) Natural freq (Mode 1497) = 137520.90000 (Hz) Natural freq (Mode 1498) = 137639.00000 (Hz) Natural freq (Mode 1499) = 138090.60000 (Hz) Natural freq (Mode 1500) = 138387.40000 (Hz) Natural freq (Mode 1501) = 138465.10000 (Hz) Natural freq (Mode 1502) = 138815.80000 (Hz) Natural freq (Mode 1503) = 138915.10000 (Hz) Natural freq (Mode 1504) = 138942.60000 (Hz) Natural freq (Mode 1505) = 139174.70000 (Hz) Natural freq (Mode 1506) = 139199.90000 (Hz) Natural freq (Mode 1507) = 139357.90000 (Hz) Natural freq (Mode 1508) = 139425.70000 (Hz) Natural freq (Mode 1509) = 139577.30000 (Hz) Natural freq (Mode 1510) = 139690.00000 (Hz) Natural freq (Mode 1511) = 139888.50000 (Hz) Natural freq (Mode 1512) = 140098.70000 (Hz) Natural freq (Mode 1513) = 140249.80000 (Hz) Natural freq (Mode 1514) = 140367.30000 (Hz) Natural freq (Mode 1515) = 140657.00000 (Hz) Natural freq (Mode 1516) = 140786.00000 (Hz) Natural freq (Mode 1517) = 141026.50000 (Hz) Natural freq (Mode 1518) = 141186.20000 (Hz) Natural freq (Mode 1519) = 141405.70000 (Hz) Natural freq (Mode 1520) = 141619.60000 (Hz) Natural freq (Mode 1521) = 141793.30000 (Hz) Natural freq (Mode 1522) = 142003.20000 (Hz) Natural freq (Mode 1523) = 142060.70000 (Hz) Natural freq (Mode 1524) = 142212.40000 (Hz) Natural freq (Mode 1525) = 142235.00000 (Hz) Natural freq (Mode 1526) = 142422.80000 (Hz) Natural freq (Mode 1527) = 142663.20000 (Hz) Natural freq (Mode 1528) = 143052.20000 (Hz) Natural freq (Mode 1529) = 143084.90000 (Hz) Natural freq (Mode 1530) = 143132.30000 (Hz) Natural freq (Mode 1531) = 143274.40000 (Hz) Natural freq (Mode 1532) = 143396.20000 (Hz) Natural freq (Mode 1533) = 143756.70000 (Hz) Natural freq (Mode 1534) = 143943.30000 (Hz) Natural freq (Mode 1535) = 144127.80000 (Hz) Natural freq (Mode 1536) = 144235.40000 (Hz) Natural freq (Mode 1537) = 144542.10000 (Hz) Natural freq (Mode 1538) = 144662.30000 (Hz) Natural freq (Mode 1539) = 144690.70000 (Hz) Natural freq (Mode 1540) = 144771.30000 (Hz) Natural freq (Mode 1541) = 145039.90000 (Hz) Natural freq (Mode 1542) = 145151.10000 (Hz) Natural freq (Mode 1543) = 145284.10000 (Hz) Natural freq (Mode 1544) = 145642.50000 (Hz) Natural freq (Mode 1545) = 146249.40000 (Hz) Natural freq (Mode 1546) = 146402.00000 (Hz) Natural freq (Mode 1547) = 146685.30000 (Hz) Natural freq (Mode 1548) = 146725.90000 (Hz) Natural freq (Mode 1549) = 146784.20000 (Hz) Natural freq (Mode 1550) = 146916.60000 (Hz) Natural freq (Mode 1551) = 147213.30000 (Hz) Natural freq (Mode 1552) = 147379.50000 (Hz) Natural freq (Mode 1553) = 147702.80000 (Hz) Natural freq (Mode 1554) = 148135.00000 (Hz) Natural freq (Mode 1555) = 148211.80000 (Hz) Natural freq (Mode 1556) = 148385.40000 (Hz) Natural freq (Mode 1557) = 148579.80000 (Hz) Natural freq (Mode 1558) = 148840.20000 (Hz) Natural freq (Mode 1559) = 148989.20000 (Hz) Natural freq (Mode 1560) = 149117.70000 (Hz) Natural freq (Mode 1561) = 149384.50000 (Hz) Natural freq (Mode 1562) = 149901.10000 (Hz) Natural freq (Mode 1563) = 150012.00000 (Hz) Natural freq (Mode 1564) = 150026.60000 (Hz) Natural freq (Mode 1565) = 150123.80000 (Hz) Natural freq (Mode 1566) = 150212.80000 (Hz) Natural freq (Mode 1567) = 150535.40000 (Hz) Natural freq (Mode 1568) = 150791.90000 (Hz) Natural freq (Mode 1569) = 151291.00000 (Hz) Natural freq (Mode 1570) = 151469.60000 (Hz) Natural freq (Mode 1571) = 151604.60000 (Hz) Natural freq (Mode 1572) = 151672.40000 (Hz) Natural freq (Mode 1573) = 151822.30000 (Hz) Natural freq (Mode 1574) = 152226.20000 (Hz) Natural freq (Mode 1575) = 152338.60000 (Hz) Natural freq (Mode 1576) = 152687.80000 (Hz) Natural freq (Mode 1577) = 152820.80000 (Hz) Natural freq (Mode 1578) = 153515.50000 (Hz) Natural freq (Mode 1579) = 153649.70000 (Hz) Natural freq (Mode 1580) = 153716.80000 (Hz) Natural freq (Mode 1581) = 154080.40000 (Hz) Natural freq (Mode 1582) = 154227.00000 (Hz) Natural freq (Mode 1583) = 154281.30000 (Hz) Natural freq (Mode 1584) = 154350.30000 (Hz) Natural freq (Mode 1585) = 154510.10000 (Hz) Natural freq (Mode 1586) = 154829.60000 (Hz) Natural freq (Mode 1587) = 155355.80000 (Hz) Natural freq (Mode 1588) = 155436.70000 (Hz) Natural freq (Mode 1589) = 155641.50000 (Hz) Natural freq (Mode 1590) = 155881.40000 (Hz) Natural freq (Mode 1591) = 155898.70000 (Hz) Natural freq (Mode 1592) = 156045.80000 (Hz) Natural freq (Mode 1593) = 156632.20000 (Hz) Natural freq (Mode 1594) = 156715.70000 (Hz) Natural freq (Mode 1595) = 156944.30000 (Hz) Natural freq (Mode 1596) = 156959.70000 (Hz) Natural freq (Mode 1597) = 157074.30000 (Hz) Natural freq (Mode 1598) = 157281.40000 (Hz) Natural freq (Mode 1599) = 157509.00000 (Hz) Natural freq (Mode 1600) = 157672.90000 (Hz) Natural freq (Mode 1601) = 157765.50000 (Hz) Natural freq (Mode 1602) = 157847.60000 (Hz) Natural freq (Mode 1603) = 157987.50000 (Hz) Natural freq (Mode 1604) = 158062.80000 (Hz) Natural freq (Mode 1605) = 158390.60000 (Hz) Natural freq (Mode 1606) = 158600.10000 (Hz) Natural freq (Mode 1607) = 158957.10000 (Hz) Natural freq (Mode 1608) = 159008.80000 (Hz) Natural freq (Mode 1609) = 159347.70000 (Hz) Natural freq (Mode 1610) = 159448.00000 (Hz) Natural freq (Mode 1611) = 160017.90000 (Hz) Natural freq (Mode 1612) = 160125.80000 (Hz) Natural freq (Mode 1613) = 160197.70000 (Hz) Natural freq (Mode 1614) = 160403.10000 (Hz) Natural freq (Mode 1615) = 160624.50000 (Hz) Natural freq (Mode 1616) = 160755.70000 (Hz) Natural freq (Mode 1617) = 160803.50000 (Hz) Natural freq (Mode 1618) = 160976.60000 (Hz) Natural freq (Mode 1619) = 161448.10000 (Hz) Natural freq (Mode 1620) = 161586.90000 (Hz) Natural freq (Mode 1621) = 161815.20000 (Hz) Natural freq (Mode 1622) = 161986.90000 (Hz) Natural freq (Mode 1623) = 162466.80000 (Hz) Natural freq (Mode 1624) = 162566.50000 (Hz) Natural freq (Mode 1625) = 162608.40000 (Hz) Natural freq (Mode 1626) = 162717.60000 (Hz) Natural freq (Mode 1627) = 162844.00000 (Hz) Natural freq (Mode 1628) = 163278.60000 (Hz) Natural freq (Mode 1629) = 163309.40000 (Hz) Natural freq (Mode 1630) = 163964.70000 (Hz) Natural freq (Mode 1631) = 164005.10000 (Hz) Natural freq (Mode 1632) = 164261.60000 (Hz) Natural freq (Mode 1633) = 164326.10000 (Hz) Natural freq (Mode 1634) = 164590.90000 (Hz) Natural freq (Mode 1635) = 164656.90000 (Hz) Natural freq (Mode 1636) = 165096.90000 (Hz) Natural freq (Mode 1637) = 165297.50000 (Hz) Natural freq (Mode 1638) = 165804.30000 (Hz) Natural freq (Mode 1639) = 166068.20000 (Hz) Natural freq (Mode 1640) = 166457.30000 (Hz) Natural freq (Mode 1641) = 166514.40000 (Hz) Natural freq (Mode 1642) = 166618.00000 (Hz) Natural freq (Mode 1643) = 167181.10000 (Hz) Natural freq (Mode 1644) = 167769.30000 (Hz) Natural freq (Mode 1645) = 167803.40000 (Hz) Natural freq (Mode 1646) = 167887.70000 (Hz) Natural freq (Mode 1647) = 167937.00000 (Hz) Natural freq (Mode 1648) = 168171.80000 (Hz) Natural freq (Mode 1649) = 168637.70000 (Hz) Natural freq (Mode 1650) = 168827.00000 (Hz) Natural freq (Mode 1651) = 168918.90000 (Hz) Natural freq (Mode 1652) = 169013.80000 (Hz) Natural freq (Mode 1653) = 169143.70000 (Hz) Natural freq (Mode 1654) = 169595.50000 (Hz) Natural freq (Mode 1655) = 169874.10000 (Hz) Natural freq (Mode 1656) = 169886.40000 (Hz) Natural freq (Mode 1657) = 169891.20000 (Hz) Natural freq (Mode 1658) = 169934.80000 (Hz) Natural freq (Mode 1659) = 170188.10000 (Hz) Natural freq (Mode 1660) = 170651.40000 (Hz) Natural freq (Mode 1661) = 170659.80000 (Hz) Natural freq (Mode 1662) = 171236.50000 (Hz) Natural freq (Mode 1663) = 171387.80000 (Hz) Natural freq (Mode 1664) = 171667.50000 (Hz) Natural freq (Mode 1665) = 171785.20000 (Hz) Natural freq (Mode 1666) = 172104.00000 (Hz) Natural freq (Mode 1667) = 172379.30000 (Hz) Natural freq (Mode 1668) = 172531.20000 (Hz) Natural freq (Mode 1669) = 173061.80000 (Hz) Natural freq (Mode 1670) = 173218.80000 (Hz) Natural freq (Mode 1671) = 173992.60000 (Hz) Natural freq (Mode 1672) = 174199.60000 (Hz) Natural freq (Mode 1673) = 174311.20000 (Hz) Natural freq (Mode 1674) = 174609.30000 (Hz) Natural freq (Mode 1675) = 174851.40000 (Hz) Natural freq (Mode 1676) = 175088.40000 (Hz) Natural freq (Mode 1677) = 175104.80000 (Hz) Natural freq (Mode 1678) = 175240.60000 (Hz) Natural freq (Mode 1679) = 175725.80000 (Hz) Natural freq (Mode 1680) = 175958.00000 (Hz) Natural freq (Mode 1681) = 176785.50000 (Hz) Natural freq (Mode 1682) = 176887.90000 (Hz) Natural freq (Mode 1683) = 176960.70000 (Hz) Natural freq (Mode 1684) = 177004.30000 (Hz) Natural freq (Mode 1685) = 177410.10000 (Hz) Natural freq (Mode 1686) = 177613.00000 (Hz) Natural freq (Mode 1687) = 177999.40000 (Hz) Natural freq (Mode 1688) = 178203.10000 (Hz) Natural freq (Mode 1689) = 178443.20000 (Hz) Natural freq (Mode 1690) = 179265.20000 (Hz) Natural freq (Mode 1691) = 179577.40000 (Hz) Natural freq (Mode 1692) = 179735.20000 (Hz) Natural freq (Mode 1693) = 179903.20000 (Hz) Natural freq (Mode 1694) = 180130.10000 (Hz) Natural freq (Mode 1695) = 180359.50000 (Hz) Natural freq (Mode 1696) = 180434.90000 (Hz) Natural freq (Mode 1697) = 181385.00000 (Hz) Natural freq (Mode 1698) = 181992.60000 (Hz) Natural freq (Mode 1699) = 182050.10000 (Hz) Natural freq (Mode 1700) = 182062.40000 (Hz) Natural freq (Mode 1701) = 183019.60000 (Hz) Natural freq (Mode 1702) = 183208.80000 (Hz) Natural freq (Mode 1703) = 183609.70000 (Hz) Natural freq (Mode 1704) = 184158.80000 (Hz) Natural freq (Mode 1705) = 184251.30000 (Hz) Natural freq (Mode 1706) = 184789.50000 (Hz) Natural freq (Mode 1707) = 184832.80000 (Hz) Natural freq (Mode 1708) = 185132.10000 (Hz) Natural freq (Mode 1709) = 185327.30000 (Hz) Natural freq (Mode 1710) = 185472.20000 (Hz) Natural freq (Mode 1711) = 185901.70000 (Hz) Natural freq (Mode 1712) = 186622.70000 (Hz) Natural freq (Mode 1713) = 187198.40000 (Hz) Natural freq (Mode 1714) = 187443.40000 (Hz) Natural freq (Mode 1715) = 187507.80000 (Hz) Natural freq (Mode 1716) = 187872.30000 (Hz) Natural freq (Mode 1717) = 188187.00000 (Hz) Natural freq (Mode 1718) = 188741.90000 (Hz) Natural freq (Mode 1719) = 188959.60000 (Hz) Natural freq (Mode 1720) = 189275.20000 (Hz) Natural freq (Mode 1721) = 190410.90000 (Hz) Natural freq (Mode 1722) = 190828.60000 (Hz) Natural freq (Mode 1723) = 191294.90000 (Hz) Natural freq (Mode 1724) = 191352.10000 (Hz) Natural freq (Mode 1725) = 191490.70000 (Hz) Natural freq (Mode 1726) = 191801.40000 (Hz) Natural freq (Mode 1727) = 192067.80000 (Hz) Natural freq (Mode 1728) = 192128.50000 (Hz) Natural freq (Mode 1729) = 192910.30000 (Hz) Natural freq (Mode 1730) = 193493.10000 (Hz) Natural freq (Mode 1731) = 193667.50000 (Hz) Natural freq (Mode 1732) = 193707.10000 (Hz) Natural freq (Mode 1733) = 194562.50000 (Hz) Natural freq (Mode 1734) = 194671.90000 (Hz) Natural freq (Mode 1735) = 194895.90000 (Hz) Natural freq (Mode 1736) = 195986.20000 (Hz) Natural freq (Mode 1737) = 196046.40000 (Hz) Natural freq (Mode 1738) = 196164.80000 (Hz) Natural freq (Mode 1739) = 196916.80000 (Hz) Natural freq (Mode 1740) = 196945.90000 (Hz) Natural freq (Mode 1741) = 196963.30000 (Hz) Natural freq (Mode 1742) = 198742.00000 (Hz) Natural freq (Mode 1743) = 198832.90000 (Hz) Natural freq (Mode 1744) = 199305.40000 (Hz) Natural freq (Mode 1745) = 200294.70000 (Hz) Natural freq (Mode 1746) = 200419.80000 (Hz) Natural freq (Mode 1747) = 201244.20000 (Hz) Natural freq (Mode 1748) = 201284.70000 (Hz) Natural freq (Mode 1749) = 201362.20000 (Hz) Natural freq (Mode 1750) = 201875.70000 (Hz) Natural freq (Mode 1751) = 202090.90000 (Hz) Natural freq (Mode 1752) = 202691.80000 (Hz) Natural freq (Mode 1753) = 203016.30000 (Hz) Natural freq (Mode 1754) = 204512.00000 (Hz) Natural freq (Mode 1755) = 205046.80000 (Hz) Natural freq (Mode 1756) = 205539.70000 (Hz) Natural freq (Mode 1757) = 206255.10000 (Hz) Natural freq (Mode 1758) = 209931.40000 (Hz) Natural freq (Mode 1759) = 210310.70000 (Hz) Natural freq (Mode 1760) = 211454.20000 (Hz) Natural freq (Mode 1761) = 211898.10000 (Hz) Natural freq (Mode 1762) = 212483.80000 (Hz) Natural freq (Mode 1763) = 213805.00000 (Hz) Natural freq (Mode 1764) = 215284.00000 (Hz) Natural freq (Mode 1765) = 216529.80000 (Hz) Natural freq (Mode 1766) = 217898.60000 (Hz) Natural freq (Mode 1767) = 219200.70000 (Hz) Natural freq (Mode 1768) = 220852.30000 (Hz) Natural freq (Mode 1769) = 222877.80000 (Hz) Natural freq (Mode 1770) = 223804.40000 (Hz) Natural freq (Mode 1771) = 230522.70000 (Hz) Natural freq (Mode 1772) = 231395.10000 (Hz) Natural freq (Mode 1773) = 234055.50000 (Hz) Natural freq (Mode 1774) = 237433.60000 (Hz) Natural freq (Mode 1775) = 240144.30000 (Hz) Natural freq (Mode 1776) = 240535.30000 (Hz) Natural freq (Mode 1777) = 243767.00000 (Hz) Natural freq (Mode 1778) = 253575.70000 (Hz) Natural freq (Mode 1779) = 267124.30000 (Hz) real 0m2.180s user 0m1.588s sys 0m0.564s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_CompositeWingFreq_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_Composite_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_Composite_PyTest.py test; + python -u nastran_Composite_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 49 Number of elements = 36 Number of triangle elements = 0 Number of quadrilateral elements = 36 ---------------------------- Total number of nodes = 49 Total number of elements = 36 Mapping Csys attributes ................ Number of unique Csys attributes = 1 Name = plate, index = 1 Getting FEA coordinate systems....... Number of coordinate systems - 1 Coordinate system name - plate Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plateTip, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 49 Number of elements = 36 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 36 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - cantilever No "constraintType" specified for Constraint tuple cantilever, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Warning: No loads specified for case EigenAnalysis!!!! Writing mass increment cards Writing analysis cards, 0 Writing combined constraint cards Writing constraint cards Writing material cards Writing property cards Writing coordinate system cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.111s user 0m0.799s sys 0m0.398s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_Composite_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_Flutter_15degree.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_Flutter_15degree.py test; + python -u nastran_Flutter_15degree.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Edge, index = 1 Name = Body, index = 2 Name = Root, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 133 Number of elements = 108 Number of triangle elements = 0 Number of quadrilateral elements = 108 Body 2 (of 2) Number of nodes = 1 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 134 Total number of elements = 108 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Root_Point, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Root_Point, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = WingSurface, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = Root, index = 1 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Edge, index = 1 Name = Body, index = 2 Name = Root, index = 3 Name = Wing, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Edge, index = 1 Name = Body, index = 2 Name = Root, index = 3 Name = Wing, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 133 Number of elements = 108 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 108 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 134 Combined Number of elements = 109 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 108 Getting vortex lattice surface data VLM surface name - WingSurface Done getting vortex lattice surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 133 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - aluminum No "materialType" specified for Material tuple aluminum, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Body Property name - Edge Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - PointConstraint No "constraintType" specified for Constraint tuple PointConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Getting FEA connections....... Number of connection tuples - 1 Connection name - Root No "groupName" specified for Connection tuple Root! Looking for automatic connections from the use of capsConnectLink for Root 7 automatic connections were made for capsConnect Root (node id 134) Done getting FEA connections Load tuple is NULL - No loads applied Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Flutter Done getting FEA analyses Writing Nastran grid and connectivity file (in free field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing connection cards - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No loads specified for case Flutter!!!! Writing mass increment cards Writing aero card Writing analysis cards, 0 Writing constraint ADD cards Writing constraint cards Writing material cards Writing property cards Writing aeroelastic cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.103s user 0m0.814s sys 0m0.380s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_Flutter_15degree.py passed (as expected) ================================================= ================================================= + echo 'nastran_MultiLoadCase_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_MultiLoadCase_PyTest.py test; + python -u nastran_MultiLoadCase_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 49 Number of elements = 36 Number of triangle elements = 0 Number of quadrilateral elements = 36 ---------------------------- Total number of nodes = 49 Total number of elements = 36 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plate, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 49 Number of elements = 36 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 36 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 5 Load name - load_0 Load name - load_1 Load name - load_2 Load name - load_3 Load name - load_4 Done getting FEA loads Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 5 Analysis name - load_0 Analysis name - load_1 Analysis name - load_2 Analysis name - load_3 Analysis name - load_4 Done getting FEA analyses Writing Nastran grid and connectivity file (in free field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No constraints specified for case load_0, assuming all constraints are applied!!!! Warning: No constraints specified for case load_1, assuming all constraints are applied!!!! Warning: No constraints specified for case load_2, assuming all constraints are applied!!!! Warning: No constraints specified for case load_3, assuming all constraints are applied!!!! Warning: No constraints specified for case load_4, assuming all constraints are applied!!!! Writing mass increment cards Writing analysis cards, 0 Writing load ADD cards Writing combined constraint cards Writing load ADD cards Writing combined constraint cards Writing load ADD cards Writing combined constraint cards Writing load ADD cards Writing combined constraint cards Writing load ADD cards Writing combined constraint cards Writing load cards Writing constraint cards Writing material cards Writing property cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.050s user 0m0.768s sys 0m0.407s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_MultiLoadCase_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_OptimizationMultiLoad_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_OptimizationMultiLoad_PyTest.py test; + python -u nastran_OptimizationMultiLoad_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 49 Number of elements = 36 Number of triangle elements = 0 Number of quadrilateral elements = 36 ---------------------------- Total number of nodes = 49 Total number of elements = 36 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plate, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 49 Number of elements = 36 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 36 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - load_0 Load name - load_1 Done getting FEA loads Getting FEA design variables....... Number of design variables - 2 Design_Variable name - materialDV Design_Variable name - propertyDV Design_Variable_Relation name - materialDVR Name madeupium not found in attribute map!!!! Design_Variable_Relation name - propertyDVR Number of design variable relations - 2 Done getting FEA design variables Getting FEA design constraints....... Number of design constraints - 2 Design_Constraint name - stress1 Design_Constraint name - stress2 Done getting FEA design constraints Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 2 Analysis name - load_0 Analysis name - load_1 Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No constraints specified for case load_0, assuming all constraints are applied!!!! Warning: No constraints specified for case load_1, assuming all constraints are applied!!!! Writing mass increment cards Writing analysis cards, 0 Writing load ADD cards Writing combined constraint cards Writing design constraint ADD cards Writing load ADD cards Writing combined constraint cards Writing design constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Writing design variable cards Writing design variable relation cards Writing design constraints and responses cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running NASTRAN! real 0m1.032s user 0m0.767s sys 0m0.391s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_OptimizationMultiLoad_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_PlateMisc_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_PlateMisc_PyTest.py test; + python -u nastran_PlateMisc_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 49 Number of elements = 36 Number of triangle elements = 0 Number of quadrilateral elements = 36 ---------------------------- Total number of nodes = 49 Total number of elements = 36 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plate, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 49 Number of elements = 36 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 36 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 3 Load name - moment Load name - pressure Load name - thermal Done getting FEA loads Getting FEA design variables....... Number of design variables - 1 Design_Variable name - pltvar Number of design variable relations - 0 Done getting FEA design variables Getting FEA design constraints....... Number of design constraints - 1 Design_Constraint name - pltcon Done getting FEA design constraints Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Nastran grid and connectivity file (in free field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Writing mass increment cards Writing analysis cards, 0 Writing load ADD cards Writing constraint ADD cards Writing design constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Writing design variable cards Writing design constraints and responses cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.097s user 0m0.796s sys 0m0.417s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_PlateMisc_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_PyTest.py test; + python -u nastran_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Ribs_and_Spars, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 2091 Number of elements = 1845 Number of triangle elements = 0 Number of quadrilateral elements = 1845 ---------------------------- Total number of nodes = 2091 Total number of elements = 1845 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Constraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Ribs_and_Spars, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2091 Number of elements = 1845 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 1845 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - Ribs_and_Spars Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - ribConstraint No "constraintType" specified for Constraint tuple ribConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Warning: No loads specified for case EigenAnalysis!!!! Writing mass increment cards Writing analysis cards, 0 Writing combined constraint cards Writing constraint cards Writing material cards Writing property cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! Getting results for natural frequencies..... Reading Nastran FO6 file - extracting Eigen-Values! Number of Eigen-Values = 10 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Loading Eigen-Value = 3 Loading Eigen-Value = 4 Loading Eigen-Value = 5 Loading Eigen-Value = 6 Loading Eigen-Value = 7 Loading Eigen-Value = 8 Loading Eigen-Value = 9 Loading Eigen-Value = 10 Natural freq (Mode 1) = 0.02165 (Hz) Natural freq (Mode 2) = 0.02165 (Hz) Natural freq (Mode 3) = 0.10665 (Hz) Natural freq (Mode 4) = 0.10665 (Hz) Natural freq (Mode 5) = 0.13547 (Hz) Natural freq (Mode 6) = 0.13547 (Hz) Natural freq (Mode 7) = 0.23092 (Hz) Natural freq (Mode 8) = 0.23092 (Hz) Natural freq (Mode 9) = 0.27609 (Hz) Natural freq (Mode 10) = 0.27609 (Hz) real 0m8.667s user 0m11.956s sys 0m3.243s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_SingleLoadCase_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_SingleLoadCase_PyTest.py test; + python -u nastran_SingleLoadCase_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 25 Number of elements = 16 Number of triangle elements = 0 Number of quadrilateral elements = 16 ---------------------------- Total number of nodes = 25 Total number of elements = 16 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = plateEdge, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = plate, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = plate, index = 1 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 25 Number of elements = 16 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 16 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - plate Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedPressure Done getting FEA loads Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Nastran grid and connectivity file (in free field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Writing mass increment cards Writing analysis cards, 0 Writing load ADD cards Writing constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.338s user 0m0.844s sys 0m0.518s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_SingleLoadCase_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_ThreeBarDesign_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_ThreeBarDesign_PyTest.py test; + python -u nastran_ThreeBarDesign_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt WARNING:: WireBody is non-manifold Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 4 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 4 Total number of elements = 0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = boundary, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 capsIgnore attribute found for edge - 3!! capsIgnore attribute found. Removing unneeded nodes and elements from mesh! Removing unused nodes... Removed 0 (out of 4) unused nodes! Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 4 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 3 Elemental Tria3 = 0 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - bar1 Property name - bar2 Property name - bar3 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - BoundaryCondition No "constraintType" specified for Constraint tuple BoundaryCondition, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedForce Done getting FEA loads Getting FEA design variables....... Number of design variables - 3 Design_Variable name - Bar1A Design_Variable name - Bar2A Design_Variable name - Bar3A Design_Variable_Relation name - Bar1A Design_Variable_Relation name - Bar2A Design_Variable_Relation name - Bar3A Number of design variable relations - 3 Done getting FEA design variables Getting FEA design constraints....... Number of design constraints - 3 Design_Constraint name - stress1 Design_Constraint name - stress2 Design_Constraint name - stress3 Done getting FEA design constraints Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - SingleLoadCase Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Writing mass increment cards Writing analysis cards, 0 Writing load ADD cards Writing constraint ADD cards Writing design constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Writing design variable cards Writing design variable relation cards Writing design constraints and responses cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.377s user 0m0.916s sys 0m0.485s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_ThreeBarDesign_PyTest.py passed (as expected) ================================================= ================================================= + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt + echo 'nastran_ThreeBarFreq_PyTest.py test;' nastran_ThreeBarFreq_PyTest.py test; + python -u nastran_ThreeBarFreq_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt WARNING:: WireBody is non-manifold Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 4 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 4 Total number of elements = 0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = boundary, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 capsIgnore attribute found for edge - 3!! capsIgnore attribute found. Removing unneeded nodes and elements from mesh! Removing unused nodes... Removed 0 (out of 4) unused nodes! Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 4 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 3 Elemental Tria3 = 0 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - bar1 Property name - bar2 Property name - bar3 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - BoundaryCondition No "constraintType" specified for Constraint tuple BoundaryCondition, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis No "analysisType" specified for Analysis tuple EigenAnalysis, defaulting to "Modal" Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Warning: No loads specified for case EigenAnalysis!!!! Writing mass increment cards Writing analysis cards, 0 Writing combined constraint cards Writing constraint cards Writing material cards Writing property cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.116s user 0m0.820s sys 0m0.427s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_ThreeBarFreq_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_ThreeBarLinkDesign_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_ThreeBarLinkDesign_PyTest.py test; + python -u nastran_ThreeBarLinkDesign_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt WARNING:: WireBody is non-manifold Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 4 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 4 Total number of elements = 0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = boundary, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 capsIgnore attribute found for edge - 3!! capsIgnore attribute found. Removing unneeded nodes and elements from mesh! Removing unused nodes... Removed 0 (out of 4) unused nodes! Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 4 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 3 Elemental Tria3 = 0 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - bar1 Property name - bar2 Property name - bar3 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - BoundaryCondition No "constraintType" specified for Constraint tuple BoundaryCondition, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedForce Done getting FEA loads Getting FEA design variables....... Number of design variables - 3 Design_Variable name - Bar1A Design_Variable name - Bar2A Design_Variable name - Bar3A Design_Variable_Relation name - Bar1A Design_Variable_Relation name - Bar2A Design_Variable_Relation name - Bar3A Number of design variable relations - 3 Done getting FEA design variables Getting FEA design constraints....... Number of design constraints - 3 Design_Constraint name - stress1 Design_Constraint name - stress2 Design_Constraint name - stress3 Done getting FEA design constraints Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - SingleLoadCase Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Writing mass increment cards Writing analysis cards, 0 Writing load ADD cards Writing constraint ADD cards Writing design constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Writing design variable cards Writing design variable relation cards Writing design constraints and responses cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.194s user 0m0.796s sys 0m0.478s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_ThreeBarLinkDesign_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_ThreeBarMultiLoad_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_ThreeBarMultiLoad_PyTest.py test; + python -u nastran_ThreeBarMultiLoad_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt WARNING:: WireBody is non-manifold Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 4 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 4 Total number of elements = 0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = boundary, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 capsIgnore attribute found for edge - 3!! capsIgnore attribute found. Removing unneeded nodes and elements from mesh! Removing unused nodes... Removed 0 (out of 4) unused nodes! Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 4 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 3 Elemental Tria3 = 0 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - bar1 Property name - bar2 Property name - bar3 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 2 Constraint name - conOne No "constraintType" specified for Constraint tuple conOne, defaulting to "ZeroDisplacement" Constraint name - conTwo No "constraintType" specified for Constraint tuple conTwo, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - loadOne Load name - loadTwo Done getting FEA loads Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 2 Analysis name - caseOne Analysis name - caseTwo Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Writing mass increment cards Writing analysis cards, 0 Writing load ADD cards Writing constraint ADD cards Writing load ADD cards Writing constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.891s user 0m1.202s sys 0m0.598s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_ThreeBarMultiLoad_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_ThreeBar_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_ThreeBar_PyTest.py test; + python -u nastran_ThreeBar_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt WARNING:: WireBody is non-manifold Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 4 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 4 Total number of elements = 0 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = boundary, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = force, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = bar1, index = 1 Name = bar2, index = 2 Name = bar3, index = 3 capsIgnore attribute found for edge - 3!! capsIgnore attribute found. Removing unneeded nodes and elements from mesh! Removing unused nodes... Removed 0 (out of 4) unused nodes! Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 4 Number of elements = 3 Elemental Nodes = 0 Elemental Rods = 3 Elemental Tria3 = 0 Elemental Quad4 = 0 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - bar1 Property name - bar2 Property name - bar3 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - BoundaryCondition No "constraintType" specified for Constraint tuple BoundaryCondition, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - appliedForce Done getting FEA loads Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - SingleLoadCase Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Writing mass increment cards Writing analysis cards, 0 Writing load ADD cards Writing constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.692s user 0m1.045s sys 0m0.609s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_ThreeBar_PyTest.py passed (as expected) ================================================= ================================================= + echo 'nastran_Trim_15degree.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nastran_Trim_15degree.py test; + python -u nastran_Trim_15degree.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Edge, index = 1 Name = Body, index = 2 Name = Root, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 117 Number of elements = 96 Number of triangle elements = 0 Number of quadrilateral elements = 96 Body 2 (of 2) Number of nodes = 1 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 118 Total number of elements = 96 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Root_Point, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Root_Point, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 1 Name = WingSurface, index = 1 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = Root, index = 1 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Edge, index = 1 Name = Body, index = 2 Name = Root, index = 3 Name = Wing, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Edge, index = 1 Name = Body, index = 2 Name = Root, index = 3 Name = Wing, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 117 Number of elements = 96 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 96 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 118 Combined Number of elements = 97 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 96 Getting vortex lattice surface data VLM surface name - WingSurface Done getting vortex lattice surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 117 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - aluminum No "materialType" specified for Material tuple aluminum, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - Body Property name - Edge Property name - Root Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - PointConstraint No "constraintType" specified for Constraint tuple PointConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Getting FEA supports....... Number of supports - 1 Support name - PointSupport Done getting FEA supports Getting FEA connections....... Number of connection tuples - 1 Connection name - Root No "groupName" specified for Connection tuple Root! Looking for automatic connections from the use of capsConnectLink for Root 9 automatic connections were made for capsConnect Root (node id 118) Done getting FEA connections Getting FEA loads....... Number of loads - 2 Load name - GravityLoad No "groupName" specified for Load tuple GravityLoad, going to use load name Load name - PointLoad Done getting FEA loads Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Trim Done getting FEA analyses Writing Nastran grid and connectivity file (in free field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing connection cards - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No loads specified for case Trim, assuming all loads are applied!!!! Writing mass increment cards Writing aeros card Writing aestat cards Writing analysis cards, 0 Writing load ADD cards Writing constraint ADD cards Writing load cards Writing constraint cards Writing support cards Writing material cards Writing property cards Writing aeroelastic cards Done writing aeroelastic cards Done writing files Running Nastran...... Done running Nastran! real 0m1.084s user 0m0.810s sys 0m0.399s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case nastran_Trim_15degree.py passed (as expected) ================================================= Running.... AEROELASTIC PyTests ================================================= + echo 'aeroelasticSimple_Pressure_SU2_and_Astros.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aeroelasticSimple_Pressure_SU2_and_Astros.py test; + python -u aeroelasticSimple_Pressure_SU2_and_Astros.py -outLevel=0 -noPlotData + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Running PreAnalysis ...... su2 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 1 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 9 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 12 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 4 5 EGADS : 2 Yes 0 0 1 0 1 1 3 5 6 EGADS : 3 Yes 0 0 1 0 1 1 2 4 6 7 8 EGADS : 4 Yes 0 0 1 0 1 1 3 5 6 EGADS : 5 Yes 0 0 1 0 1 1 2 4 6 EGADS : 6 Yes 0 0 1 0 1 2 3 4 5 EGADS : 7 Yes 0 0 1 0 1 3 8 9 EGADS : 8 Yes 0 0 1 0 1 3 7 9 EGADS : 9 Yes 0 0 1 0 1 7 8 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 1 2 -3 -4 EGADS : 2 5 6 -7 -1 EGADS : 3 -2 7 9 -8 -10 -11 EGADS : 4 -12 3 8 -13 EGADS : 5 4 12 -14 -5 EGADS : 6 -6 14 13 -9 EGADS : 7 15 10 -17 -16 EGADS : 8 17 11 -15 -18 EGADS : 9 16 18 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 4 EGADS : 4 5 EGADS : 5 6 EGADS : 6 7 EGADS : 7 8 EGADS : 8 9 EGADS : 9 10 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes 1 2 -3 -4 EGADS : 2 Yes 5 6 -7 -1 EGADS : 3 Yes -2 7 9 -8 EGADS : 4 Yes -10 -11 EGADS : 5 Yes -12 3 8 -13 EGADS : 6 Yes 4 12 -14 -5 EGADS : 7 Yes -6 14 13 -9 EGADS : 8 Yes 15 10 -17 -16 EGADS : 9 Yes 17 11 -15 -18 EGADS : 10 Yes 16 18 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 2 1 1 1 2 EGADS : 2 0 Yes 1 3 1 1 3 EGADS : 3 0 Yes 4 3 1 1 4 EGADS : 4 0 Yes 2 4 1 1 5 EGADS : 5 0 Yes 2 5 1 2 5 EGADS : 6 0 Yes 5 6 1 2 6 EGADS : 7 0 Yes 1 6 1 2 3 EGADS : 8 0 Yes 3 7 1 3 4 EGADS : 9 0 Yes 6 7 1 3 6 EGADS : 10 0 Yes 8 9 1 3 7 EGADS : 11 0 Yes 9 8 1 3 8 EGADS : 12 0 Yes 4 10 1 4 5 EGADS : 13 0 Yes 10 7 1 4 6 EGADS : 14 0 Yes 5 10 1 5 6 EGADS : 15 0 Yes 11 8 1 7 8 EGADS : 16 0 Yes 11 12 1 7 9 EGADS : 17 0 Yes 12 9 1 7 8 EGADS : 18 0 Yes 12 11 1 8 9 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 0 0 0 EGADS : 2 Yes 0 40 0 EGADS : 3 Yes 0 0 20 EGADS : 4 Yes 0 40 20 EGADS : 5 Yes 20 40 0 EGADS : 6 Yes 20 0 0 EGADS : 7 Yes 20 0 20 EGADS : 8 Yes 1.61374306 0 0 EGADS : 9 Yes 0 0 0 EGADS : 10 Yes 20 40 20 EGADS : 11 Yes 2.53650745 3.87298335 0.334116517 EGADS : 12 Yes 1.57194608 3.87298335 0.249728332 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 40 AFLR4 : Min Bounding Box Length = 40 AFLR4 : Max Ref Bounding Box Length = 40 AFLR4 : Min Ref Bounding Box Length = 40 AFLR4 : Reference Length = 1.61374 AFLR4 : BL Thickness = 0 AFLR4 : Abs Min Surf Spacing = 0.00403436 AFLR4 : Min Surf Spacing = 0.161374 AFLR4 : Max Surf Spacing = 1.21031 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Nodes, Trias,Quads= 1293 2452 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Nodes, Trias,Quads= 1298 2462 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 3418 6687 0 AFLR4 : Nodes, Trias,Quads= 3008 5867 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1315 2496 0 AFLR4 : Nodes, Trias,Quads= 1297 2460 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Nodes, Trias,Quads= 1298 2462 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1319 2504 0 AFLR4 : Nodes, Trias,Quads= 1294 2454 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 200 344 0 AFLR4 : Nodes, Trias,Quads= 160 264 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 193 330 0 AFLR4 : Nodes, Trias,Quads= 155 254 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 17 21 0 AFLR4 : Nodes, Trias,Quads= 11 9 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 9344 18684 928 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 9344 18684 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1335 2536 0 AFLR4 : Nodes, Trias,Quads= 1317 2500 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1337 2540 0 AFLR4 : Nodes, Trias,Quads= 1320 2506 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 3787 7420 0 AFLR4 : Nodes, Trias,Quads= 2943 5732 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1341 2548 0 AFLR4 : Nodes, Trias,Quads= 1321 2508 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 1337 2540 0 AFLR4 : Nodes, Trias,Quads= 1320 2506 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1342 2550 0 AFLR4 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 233 404 0 AFLR4 : Nodes, Trias,Quads= 210 358 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 224 386 0 AFLR4 : Nodes, Trias,Quads= 196 330 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 18 22 0 AFLR4 : Nodes, Trias,Quads= 12 10 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 9478 18952 946 OVERALL : CPU Time = 0.311 seconds Body 1 (of 1) Number of nodes = 9478 Number of elements = 18952 Number of triangle elements = 18952 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 9478 Total number of elements = 18952 Total number of triangle elements = 18952 Total number of quadrilateral elements = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 61788 Number of elements = 355965 Number of triangles = 18952 Number of quadrilatarals = 0 Number of tetrahedrals = 337013 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Skin Boundary condition name - SymmPlane Done getting CFD boundary conditions Info: No recognized data transfer names found. Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Pressure_SA.dat. Surface file name: surface_flow_aeroelasticSimple_Pressure_SA. Volume file name: flow_aeroelasticSimple_Pressure_SA. Restart file name: restart_flow_aeroelasticSimple_Pressure_SA.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 61788 grid points. 337013 volume elements. 3 surface markers. 12522 boundary elements in index 0 (Marker = BC_1). 5732 boundary elements in index 1 (Marker = BC_2). 698 boundary elements in index 2 (Marker = BC_3). 337013 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 63999.5. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 83.4538. Mean K: 0.863308. Standard deviation K: 5.00657. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 54.7348| 86.7581| | CV Face Area Aspect Ratio| 1.06698| 21.5651| | CV Sub-Volume Ratio| 1| 6.22786| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 61788| 1/1.00| 10| | 1| 10504| 1/5.88| 8.3095| | 2| 1841| 1/5.71| 6.97535| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 9.2451 m^2. Area projection in the x-plane = 0.651846 m^2, y-plane = 0.30478 m^2, z-plane = 4.4157 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.38 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.86329e-18 m, z-direction = -0.0467611 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 2.2771e+00| -1.361370| 0.918961| 0.580745| 4.107735| -0.945745| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.3739e+00| -1.753698| 0.759192| 0.409261| 3.702741| -0.508573| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.3051e+00| -1.769228| 0.570930| 0.229342| 3.687595| 1.615844| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.76923| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Pressure_SA.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SA.dat). |CSV file |surface_flow_aeroelasticSimple_Pressure_SA.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SA.dat). |Tecplot binary |flow_aeroelasticSimple_Pressure_SA.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SA.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Pressure_SA.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SA.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running ...... astros Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 180 Number of elements = 194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 32 Elemental Quad4 = 162 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Rib_Root Property name - Skin Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureAero No "groupName" specified for Load tuple pressureAero, going to use load name Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SA.csv Number of variables = 16 Number of data points = 361 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 3.101708e+09, tgt = 3.101708e+09, diff = 1.858783e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SA.csv Number of variables = 16 Number of data points = 361 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 3.017715e+09, tgt = 3.017715e+09, diff = 2.021653e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SA.csv Number of variables = 16 Number of data points = 361 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 4.373425e+07, tgt = 4.373425e+07, diff = 2.773415e-02 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 81 (total = 81) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 81 (total = 162) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 16 (total = 178) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL real 0m25.422s user 0m23.624s sys 0m2.652s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelasticSimple_Pressure_SU2_and_Astros.py passed (as expected) ================================================= ================================================= + echo 'aeroelasticSimple_Displacement_SU2_and_Astros.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aeroelasticSimple_Displacement_SU2_and_Astros.py test; + python -u aeroelasticSimple_Displacement_SU2_and_Astros.py -outLevel=0 -noPlotData + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Running PreAnalysis ...... astros Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 180 Number of elements = 194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 32 Elemental Quad4 = 162 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Rib_Root Property name - Skin Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureInternal Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Running Astros...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Running PostAnalysis ...... astros Running PreAnalysis ...... su2 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 1 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 9 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 12 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 4 5 EGADS : 2 Yes 0 0 1 0 1 1 3 5 6 EGADS : 3 Yes 0 0 1 0 1 1 2 4 6 7 8 EGADS : 4 Yes 0 0 1 0 1 1 3 5 6 EGADS : 5 Yes 0 0 1 0 1 1 2 4 6 EGADS : 6 Yes 0 0 1 0 1 2 3 4 5 EGADS : 7 Yes 0 0 1 0 1 3 8 9 EGADS : 8 Yes 0 0 1 0 1 3 7 9 EGADS : 9 Yes 0 0 1 0 1 7 8 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 1 2 -3 -4 EGADS : 2 5 6 -7 -1 EGADS : 3 -2 7 9 -8 -10 -11 EGADS : 4 -12 3 8 -13 EGADS : 5 4 12 -14 -5 EGADS : 6 -6 14 13 -9 EGADS : 7 15 10 -17 -16 EGADS : 8 17 11 -15 -18 EGADS : 9 16 18 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 4 EGADS : 4 5 EGADS : 5 6 EGADS : 6 7 EGADS : 7 8 EGADS : 8 9 EGADS : 9 10 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes 1 2 -3 -4 EGADS : 2 Yes 5 6 -7 -1 EGADS : 3 Yes -2 7 9 -8 EGADS : 4 Yes -10 -11 EGADS : 5 Yes -12 3 8 -13 EGADS : 6 Yes 4 12 -14 -5 EGADS : 7 Yes -6 14 13 -9 EGADS : 8 Yes 15 10 -17 -16 EGADS : 9 Yes 17 11 -15 -18 EGADS : 10 Yes 16 18 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 2 1 1 1 2 EGADS : 2 0 Yes 1 3 1 1 3 EGADS : 3 0 Yes 4 3 1 1 4 EGADS : 4 0 Yes 2 4 1 1 5 EGADS : 5 0 Yes 2 5 1 2 5 EGADS : 6 0 Yes 5 6 1 2 6 EGADS : 7 0 Yes 1 6 1 2 3 EGADS : 8 0 Yes 3 7 1 3 4 EGADS : 9 0 Yes 6 7 1 3 6 EGADS : 10 0 Yes 8 9 1 3 7 EGADS : 11 0 Yes 9 8 1 3 8 EGADS : 12 0 Yes 4 10 1 4 5 EGADS : 13 0 Yes 10 7 1 4 6 EGADS : 14 0 Yes 5 10 1 5 6 EGADS : 15 0 Yes 11 8 1 7 8 EGADS : 16 0 Yes 11 12 1 7 9 EGADS : 17 0 Yes 12 9 1 7 8 EGADS : 18 0 Yes 12 11 1 8 9 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 0 0 0 EGADS : 2 Yes 0 40 0 EGADS : 3 Yes 0 0 20 EGADS : 4 Yes 0 40 20 EGADS : 5 Yes 20 40 0 EGADS : 6 Yes 20 0 0 EGADS : 7 Yes 20 0 20 EGADS : 8 Yes 1.61374306 0 0 EGADS : 9 Yes 0 0 0 EGADS : 10 Yes 20 40 20 EGADS : 11 Yes 2.53650745 3.87298335 0.334116517 EGADS : 12 Yes 1.57194608 3.87298335 0.249728332 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 40 AFLR4 : Min Bounding Box Length = 40 AFLR4 : Max Ref Bounding Box Length = 40 AFLR4 : Min Ref Bounding Box Length = 40 AFLR4 : Reference Length = 1.61374 AFLR4 : BL Thickness = 0 AFLR4 : Abs Min Surf Spacing = 0.00403436 AFLR4 : Min Surf Spacing = 0.161374 AFLR4 : Max Surf Spacing = 1.21031 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Nodes, Trias,Quads= 1293 2452 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Nodes, Trias,Quads= 1298 2462 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 3418 6687 0 AFLR4 : Nodes, Trias,Quads= 3008 5867 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1315 2496 0 AFLR4 : Nodes, Trias,Quads= 1297 2460 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Nodes, Trias,Quads= 1298 2462 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1319 2504 0 AFLR4 : Nodes, Trias,Quads= 1294 2454 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 200 344 0 AFLR4 : Nodes, Trias,Quads= 160 264 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 193 330 0 AFLR4 : Nodes, Trias,Quads= 155 254 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 17 21 0 AFLR4 : Nodes, Trias,Quads= 11 9 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 9344 18684 928 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 9344 18684 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1335 2536 0 AFLR4 : Nodes, Trias,Quads= 1317 2500 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1337 2540 0 AFLR4 : Nodes, Trias,Quads= 1320 2506 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 3787 7420 0 AFLR4 : Nodes, Trias,Quads= 2943 5732 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1341 2548 0 AFLR4 : Nodes, Trias,Quads= 1321 2508 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 1337 2540 0 AFLR4 : Nodes, Trias,Quads= 1320 2506 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1342 2550 0 AFLR4 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 233 404 0 AFLR4 : Nodes, Trias,Quads= 210 358 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 224 386 0 AFLR4 : Nodes, Trias,Quads= 196 330 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 18 22 0 AFLR4 : Nodes, Trias,Quads= 12 10 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 9478 18952 946 OVERALL : CPU Time = 0.351 seconds Body 1 (of 1) Number of nodes = 9478 Number of elements = 18952 Number of triangle elements = 18952 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 9478 Total number of elements = 18952 Total number of triangle elements = 18952 Total number of quadrilateral elements = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 61788 Number of elements = 355965 Number of triangles = 18952 Number of quadrilatarals = 0 Number of tetrahedrals = 337013 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Skin Boundary condition name - SymmPlane Done getting CFD boundary conditions Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticSimple_Displacement_SA_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 61788 grid points. 337013 volume elements. 3 surface markers. 12522 boundary elements in index 0 (Marker = BC_1). 5732 boundary elements in index 1 (Marker = BC_2). 698 boundary elements in index 2 (Marker = BC_3). 337013 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 26.027356 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Displacement_SA.dat. Surface file name: surface_flow_aeroelasticSimple_Displacement_SA. Volume file name: flow_aeroelasticSimple_Displacement_SA. Restart file name: restart_flow_aeroelasticSimple_Displacement_SA.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 61788 grid points. 337013 volume elements. 3 surface markers. 12522 boundary elements in index 0 (Marker = BC_1). 5732 boundary elements in index 1 (Marker = BC_2). 698 boundary elements in index 2 (Marker = BC_3). 337013 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 63997.8. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 83.9101. Mean K: 0.903752. Standard deviation K: 4.4801. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 42.7246| 86.7623| | CV Face Area Aspect Ratio| 1.05988| 23.4731| | CV Sub-Volume Ratio| 1| 155.18| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 61788| 1/1.00| 10| | 1| 10504| 1/5.88| 8.3095| | 2| 1841| 1/5.71| 6.97535| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.89892 m. Wetted area = 11.6151 m^2. Area projection in the x-plane = 2.90002 m^2, y-plane = 1.28883 m^2, z-plane = 4.27937 m^2. Max. coordinate in the x-direction = 2.53729 m, y-direction = 3.89892 m, z-direction = 0.526515 m. Min. coordinate in the x-direction = 0.000170858 m, y-direction = -2.86329e-18 m, z-direction = -0.706552 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 2.8661e+00| -0.691634| 1.737097| 1.249935| 4.777472| 0.053881| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.4575e+00| -1.143706| 1.454258| 1.101774| 4.327378| 0.043383| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.3178e+00| -1.163565| 1.229507| 0.914066| 4.302377| 0.103716| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.16356| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Displacement_SA.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SA.dat). |CSV file |surface_flow_aeroelasticSimple_Displacement_SA.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SA.dat). |Tecplot binary |flow_aeroelasticSimple_Displacement_SA.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SA.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Displacement_SA.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SA.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 real 1m0.107s user 0m51.927s sys 0m8.621s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelasticSimple_Displacement_SU2_and_Astros.py passed (as expected) ================================================= ================================================= + echo 'aeroelasticSimple_Iterative_SU2_and_Astros.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aeroelasticSimple_Iterative_SU2_and_Astros.py test; + python -u aeroelasticSimple_Iterative_SU2_and_Astros.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Running PreAnalysis ...... su2 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 1 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 9 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 12 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 4 5 EGADS : 2 Yes 0 0 1 0 1 1 3 5 6 EGADS : 3 Yes 0 0 1 0 1 1 2 4 6 7 8 EGADS : 4 Yes 0 0 1 0 1 1 3 5 6 EGADS : 5 Yes 0 0 1 0 1 1 2 4 6 EGADS : 6 Yes 0 0 1 0 1 2 3 4 5 EGADS : 7 Yes 0 0 1 0 1 3 8 9 EGADS : 8 Yes 0 0 1 0 1 3 7 9 EGADS : 9 Yes 0 0 1 0 1 7 8 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 1 2 -3 -4 EGADS : 2 5 6 -7 -1 EGADS : 3 -2 7 9 -8 -10 -11 EGADS : 4 -12 3 8 -13 EGADS : 5 4 12 -14 -5 EGADS : 6 -6 14 13 -9 EGADS : 7 15 10 -17 -16 EGADS : 8 17 11 -15 -18 EGADS : 9 16 18 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 4 EGADS : 4 5 EGADS : 5 6 EGADS : 6 7 EGADS : 7 8 EGADS : 8 9 EGADS : 9 10 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes 1 2 -3 -4 EGADS : 2 Yes 5 6 -7 -1 EGADS : 3 Yes -2 7 9 -8 EGADS : 4 Yes -10 -11 EGADS : 5 Yes -12 3 8 -13 EGADS : 6 Yes 4 12 -14 -5 EGADS : 7 Yes -6 14 13 -9 EGADS : 8 Yes 15 10 -17 -16 EGADS : 9 Yes 17 11 -15 -18 EGADS : 10 Yes 16 18 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 2 1 1 1 2 EGADS : 2 0 Yes 1 3 1 1 3 EGADS : 3 0 Yes 4 3 1 1 4 EGADS : 4 0 Yes 2 4 1 1 5 EGADS : 5 0 Yes 2 5 1 2 5 EGADS : 6 0 Yes 5 6 1 2 6 EGADS : 7 0 Yes 1 6 1 2 3 EGADS : 8 0 Yes 3 7 1 3 4 EGADS : 9 0 Yes 6 7 1 3 6 EGADS : 10 0 Yes 8 9 1 3 7 EGADS : 11 0 Yes 9 8 1 3 8 EGADS : 12 0 Yes 4 10 1 4 5 EGADS : 13 0 Yes 10 7 1 4 6 EGADS : 14 0 Yes 5 10 1 5 6 EGADS : 15 0 Yes 11 8 1 7 8 EGADS : 16 0 Yes 11 12 1 7 9 EGADS : 17 0 Yes 12 9 1 7 8 EGADS : 18 0 Yes 12 11 1 8 9 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 0 0 0 EGADS : 2 Yes 0 40 0 EGADS : 3 Yes 0 0 20 EGADS : 4 Yes 0 40 20 EGADS : 5 Yes 20 40 0 EGADS : 6 Yes 20 0 0 EGADS : 7 Yes 20 0 20 EGADS : 8 Yes 1.61374306 0 0 EGADS : 9 Yes 0 0 0 EGADS : 10 Yes 20 40 20 EGADS : 11 Yes 2.53650745 3.87298335 0.334116517 EGADS : 12 Yes 1.57194608 3.87298335 0.249728332 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 40 AFLR4 : Min Bounding Box Length = 40 AFLR4 : Max Ref Bounding Box Length = 40 AFLR4 : Min Ref Bounding Box Length = 40 AFLR4 : Reference Length = 1.61374 AFLR4 : BL Thickness = 0 AFLR4 : Abs Min Surf Spacing = 0.00403436 AFLR4 : Min Surf Spacing = 0.161374 AFLR4 : Max Surf Spacing = 1.21031 AFLR4 : Global Scale Factor = 2 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 376 682 0 AFLR4 : Nodes, Trias,Quads= 381 692 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 374 678 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 927 1777 0 AFLR4 : Nodes, Trias,Quads= 821 1565 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 376 682 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 374 678 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 376 682 0 AFLR4 : Nodes, Trias,Quads= 378 686 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 63 96 0 AFLR4 : Nodes, Trias,Quads= 55 80 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 64 96 0 AFLR4 : Nodes, Trias,Quads= 57 82 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 11 13 0 AFLR4 : Nodes, Trias,Quads= 7 5 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 2592 5180 482 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 2592 5180 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 385 700 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 383 696 0 AFLR4 : Nodes, Trias,Quads= 381 692 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 1004 1929 0 AFLR4 : Nodes, Trias,Quads= 955 1831 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 381 692 0 AFLR4 : Nodes, Trias,Quads= 378 686 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 386 702 0 AFLR4 : Nodes, Trias,Quads= 379 688 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 382 694 0 AFLR4 : Nodes, Trias,Quads= 379 688 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 74 115 0 AFLR4 : Nodes, Trias,Quads= 65 97 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 75 116 0 AFLR4 : Nodes, Trias,Quads= 63 92 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 2737 5470 490 OVERALL : CPU Time = 0.187 seconds Body 1 (of 1) Number of nodes = 2737 Number of elements = 5470 Number of triangle elements = 5470 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 2737 Total number of elements = 5470 Total number of triangle elements = 5470 Total number of quadrilateral elements = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 11189 Number of elements = 63352 Number of triangles = 5470 Number of quadrilatarals = 0 Number of tetrahedrals = 57882 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Skin Boundary condition name - SymmPlane Done getting CFD boundary conditions Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticSimple_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative.dat. Surface file name: surface_flow_aeroelasticSimple_Iterative. Volume file name: flow_aeroelasticSimple_Iterative. Restart file name: restart_flow_aeroelasticSimple_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 63999.5. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 47.1143. Mean K: 0.755831. Standard deviation K: 3.51256. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 50.9576| 84.7141| | CV Face Area Aspect Ratio| 1.07213| 21.5536| | CV Sub-Volume Ratio| 1| 10.2891| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11189| 1/1.00| 10| | 1| 1972| 1/5.67| 8.41001| | 2| 394| 1/5.01| 7.37481| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 8.08979 m^2. Area projection in the x-plane = 0.572014 m^2, y-plane = 0.261888 m^2, z-plane = 3.84035 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380358 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.8602e-18 m, z-direction = -0.0467106 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.7272e-01| -0.788239| 1.511706| 1.187262| 4.680867| -1.151636| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.5110e-01| -1.114115| 1.416686| 1.030318| 4.340813| -0.880779| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.4857e-01| -1.184774| 1.271379| 0.880364| 4.266950| -0.265222| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.18477| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |CSV file |surface_flow_aeroelasticSimple_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary |flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 180 Number of elements = 194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 32 Elemental Quad4 = 162 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Rib_Root Property name - Skin Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureAero No "groupName" specified for Load tuple pressureAero, going to use load name Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 3.096416e+09, tgt = 3.096415e+09, diff = 1.073042e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 3.009946e+09, tgt = 3.009946e+09, diff = 2.106818e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 4.109924e+07, tgt = 4.109924e+07, diff = 1.236494e-01 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 81 (total = 81) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 81 (total = 162) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 16 (total = 178) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticSimple_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 1.362918 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative.dat. Surface file name: surface_flow_aeroelasticSimple_Iterative. Volume file name: flow_aeroelasticSimple_Iterative. Restart file name: restart_flow_aeroelasticSimple_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 959 TETRAHEDRON volume elements. There has been a re-orientation of 51 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 64528. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 26.5359. Mean K: 0.52967. Standard deviation K: 1.76188. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 3.57703| 84.8668| | CV Face Area Aspect Ratio| 1.06228| 397.662| | CV Sub-Volume Ratio| 1| 3693.18| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11189| 1/1.00| 10| | 1| 1970| 1/5.68| 8.40717| | 2| 394| 1/5| 7.37481| +-------------------------------------------+ Finding max control volume width. Semi-span length = 4.41651 m. Wetted area = 165.461 m^2. Area projection in the x-plane = 65.909 m^2, y-plane = 36.9308 m^2, z-plane = 5.43389 m^2. Max. coordinate in the x-direction = 2.7212 m, y-direction = 4.41651 m, z-direction = 18.1582 m. Min. coordinate in the x-direction = -0.739572 m, y-direction = -0.0620634 m, z-direction = -19.0371 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.4770e-01| 1.853605| 4.808189| 4.873938| 7.322711| -0.010914| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.4886e-01| 2.158629| 4.741718| 4.915208| 7.657720| -0.029122| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.5869e-01| 2.349932| 4.816196| 4.782367| 7.732429| -0.070902| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 2.34993| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |CSV file |surface_flow_aeroelasticSimple_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary |flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). +-----------------------------------------------------------------------+ Warning: there are 31 non-physical points in the solution. Warning: 2 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 2.064700e+09, tgt = 2.064700e+09, diff = 1.259066e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 1.544262e+09, tgt = 1.544262e+09, diff = 3.041722e+00 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 2.280527e+07, tgt = 2.280527e+07, diff = 8.781843e-03 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 81 (total = 81) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 81 (total = 162) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 16 (total = 178) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticSimple_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. There has been a re-orientation of 959 TETRAHEDRON volume elements. There has been a re-orientation of 51 TRIANGLE surface elements. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 64528. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 7.761708 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative.dat. Surface file name: surface_flow_aeroelasticSimple_Iterative. Volume file name: flow_aeroelasticSimple_Iterative. Restart file name: restart_flow_aeroelasticSimple_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 22651 TETRAHEDRON volume elements. There has been a re-orientation of 1173 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 139326. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 155.346. Mean K: 1.5774. Standard deviation K: 7.35704. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 2.17622| 84.0844| | CV Face Area Aspect Ratio| 1.46454| 1585.46| | CV Sub-Volume Ratio| 1| 98320.3| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11189| 1/1.00| 10| | 1| 1988| 1/5.63| 8.43269| | 2| 408| 1/4.87| 7.46115| +-------------------------------------------+ Finding max control volume width. Semi-span length = 1.38681 m. Wetted area = 523.796 m^2. Area projection in the x-plane = 230.038 m^2, y-plane = 79.8096 m^2, z-plane = 6.63348 m^2. Max. coordinate in the x-direction = 8.71276 m, y-direction = 1.38681 m, z-direction = 118.362 m. Min. coordinate in the x-direction = 0.0330272 m, y-direction = -7.946 m, z-direction = -0.858419 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.7585e-01| 2.952787| 5.916503| 5.925140| 8.421893| -0.254645| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.7786e-01| 3.442936| 6.030135| 6.000298| 8.838401| -0.220818| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.8128e-01| 3.562615| 6.168302| 6.086319| 8.966328| -0.193914| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 3.56261| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |CSV file |surface_flow_aeroelasticSimple_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary |flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). +-----------------------------------------------------------------------+ Warning: there are 436 non-physical points in the solution. Warning: 18 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 2.087986e+09, tgt = 2.087985e+09, diff = 5.493975e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 1.695766e+09, tgt = 1.695766e+09, diff = 8.276410e+01 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 1.753619e+07, tgt = 1.753619e+07, diff = 1.487993e-04 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 81 (total = 81) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 81 (total = 162) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 16 (total = 178) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticSimple_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. There has been a re-orientation of 22651 TETRAHEDRON volume elements. There has been a re-orientation of 1173 TRIANGLE surface elements. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 139326. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 41.960785 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative.dat. Surface file name: surface_flow_aeroelasticSimple_Iterative. Volume file name: flow_aeroelasticSimple_Iterative. Restart file name: restart_flow_aeroelasticSimple_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 33373 TETRAHEDRON volume elements. There has been a re-orientation of 3503 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 1.26188e+12. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 46.3582. Mean K: 0.351963. Standard deviation K: 1.75997. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.467366| 84.5943| | CV Face Area Aspect Ratio| 1.58521| 480468| | CV Sub-Volume Ratio| 1| 1.23326e+06| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11189| 1/1.00| 10| | 1| 2000| 1/5.59| 8.44963| | 2| 414| 1/4.83| 7.49754| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.2382 m. Wetted area = 63827 m^2. Area projection in the x-plane = 45829.5 m^2, y-plane = 5453.15 m^2, z-plane = 435.098 m^2. Max. coordinate in the x-direction = 23.2403 m, y-direction = 3.2382 m, z-direction = 1540.19 m. Min. coordinate in the x-direction = -2.17316 m, y-direction = -114.437 m, z-direction = -0.179221 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.9825e-01| 7.719292| 10.686148| 10.633344| 13.188398| -0.039434| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 4.1736e-01| 8.221627| 10.706445| 10.637616| 13.707352| -0.042749| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 4.1598e-01| 8.277206| 10.818296| 10.544196| 13.587094| -0.044207| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 8.27721| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |CSV file |surface_flow_aeroelasticSimple_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary |flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). +-----------------------------------------------------------------------+ Warning: there are 635 non-physical points in the solution. Warning: 35 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Cl = 13098.742528 Cd = -296305.688432 real 1m13.209s user 1m8.632s sys 0m4.435s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_SU2_and_Astros.py passed (as expected) ================================================= ================================================= + echo 'aeroelastic_Iterative_SU2_and_Astros.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aeroelastic_Iterative_SU2_and_Astros.py test; + python -u aeroelastic_Iterative_SU2_and_Astros.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Running PreAnalysis ...... su2 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 1 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 9 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 12 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 4 5 EGADS : 2 Yes 0 0 1 0 1 1 3 5 6 EGADS : 3 Yes 0 0 1 0 1 1 2 4 6 7 8 EGADS : 4 Yes 0 0 1 0 1 1 3 5 6 EGADS : 5 Yes 0 0 1 0 1 1 2 4 6 EGADS : 6 Yes 0 0 1 0 1 2 3 4 5 EGADS : 7 Yes 0 0 1 0 1 3 8 9 EGADS : 8 Yes 0 0 1 0 1 3 7 9 EGADS : 9 Yes 0 0 1 0 1 7 8 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 1 2 -3 -4 EGADS : 2 5 6 -7 -1 EGADS : 3 -2 7 9 -8 -10 -11 EGADS : 4 -12 3 8 -13 EGADS : 5 4 12 -14 -5 EGADS : 6 -6 14 13 -9 EGADS : 7 15 10 -17 -16 EGADS : 8 17 11 -15 -18 EGADS : 9 16 18 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 4 EGADS : 4 5 EGADS : 5 6 EGADS : 6 7 EGADS : 7 8 EGADS : 8 9 EGADS : 9 10 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes 1 2 -3 -4 EGADS : 2 Yes 5 6 -7 -1 EGADS : 3 Yes -2 7 9 -8 EGADS : 4 Yes -10 -11 EGADS : 5 Yes -12 3 8 -13 EGADS : 6 Yes 4 12 -14 -5 EGADS : 7 Yes -6 14 13 -9 EGADS : 8 Yes 15 10 -17 -16 EGADS : 9 Yes 17 11 -15 -18 EGADS : 10 Yes 16 18 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 2 1 1 1 2 EGADS : 2 0 Yes 1 3 1 1 3 EGADS : 3 0 Yes 4 3 1 1 4 EGADS : 4 0 Yes 2 4 1 1 5 EGADS : 5 0 Yes 2 5 1 2 5 EGADS : 6 0 Yes 5 6 1 2 6 EGADS : 7 0 Yes 1 6 1 2 3 EGADS : 8 0 Yes 3 7 1 3 4 EGADS : 9 0 Yes 6 7 1 3 6 EGADS : 10 0 Yes 8 9 1 3 7 EGADS : 11 0 Yes 9 8 1 3 8 EGADS : 12 0 Yes 4 10 1 4 5 EGADS : 13 0 Yes 10 7 1 4 6 EGADS : 14 0 Yes 5 10 1 5 6 EGADS : 15 0 Yes 11 8 1 7 8 EGADS : 16 0 Yes 11 12 1 7 9 EGADS : 17 0 Yes 12 9 1 7 8 EGADS : 18 0 Yes 12 11 1 8 9 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 0 0 0 EGADS : 2 Yes 0 40 0 EGADS : 3 Yes 0 0 20 EGADS : 4 Yes 0 40 20 EGADS : 5 Yes 20 40 0 EGADS : 6 Yes 20 0 0 EGADS : 7 Yes 20 0 20 EGADS : 8 Yes 1.61374306 0 0 EGADS : 9 Yes 0 0 0 EGADS : 10 Yes 20 40 20 EGADS : 11 Yes 2.53650745 3.87298335 0.334116517 EGADS : 12 Yes 1.57194608 3.87298335 0.249728332 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 40 AFLR4 : Min Bounding Box Length = 40 AFLR4 : Max Ref Bounding Box Length = 40 AFLR4 : Min Ref Bounding Box Length = 40 AFLR4 : Reference Length = 1.61374 AFLR4 : BL Thickness = 0 AFLR4 : Abs Min Surf Spacing = 0.00403436 AFLR4 : Min Surf Spacing = 0.161374 AFLR4 : Max Surf Spacing = 1.21031 AFLR4 : Global Scale Factor = 2 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 376 682 0 AFLR4 : Nodes, Trias,Quads= 381 692 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 374 678 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 927 1777 0 AFLR4 : Nodes, Trias,Quads= 821 1565 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 376 682 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 374 678 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 376 682 0 AFLR4 : Nodes, Trias,Quads= 378 686 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 63 96 0 AFLR4 : Nodes, Trias,Quads= 55 80 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 64 96 0 AFLR4 : Nodes, Trias,Quads= 57 82 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 11 13 0 AFLR4 : Nodes, Trias,Quads= 7 5 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 2592 5180 482 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 2592 5180 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 385 700 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 383 696 0 AFLR4 : Nodes, Trias,Quads= 381 692 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 1004 1929 0 AFLR4 : Nodes, Trias,Quads= 955 1831 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 381 692 0 AFLR4 : Nodes, Trias,Quads= 378 686 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 386 702 0 AFLR4 : Nodes, Trias,Quads= 379 688 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 382 694 0 AFLR4 : Nodes, Trias,Quads= 379 688 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 74 115 0 AFLR4 : Nodes, Trias,Quads= 65 97 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 75 116 0 AFLR4 : Nodes, Trias,Quads= 63 92 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 2737 5470 490 OVERALL : CPU Time = 0.150 seconds Body 1 (of 1) Number of nodes = 2737 Number of elements = 5470 Number of triangle elements = 5470 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 2737 Total number of elements = 5470 Total number of triangle elements = 5470 Total number of quadrilateral elements = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 11189 Number of elements = 63352 Number of triangles = 5470 Number of quadrilatarals = 0 Number of tetrahedrals = 57882 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Skin Boundary condition name - SymmPlane Done getting CFD boundary conditions Writing SU2 data transfer files Writing SU2 Motion File - aeroelastic_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelastic_Iterative.dat. Surface file name: surface_flow_aeroelastic_Iterative. Volume file name: flow_aeroelastic_Iterative. Restart file name: restart_flow_aeroelastic_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 63999.5. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 47.1143. Mean K: 0.755831. Standard deviation K: 3.51256. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 50.9576| 84.7141| | CV Face Area Aspect Ratio| 1.07213| 21.5536| | CV Sub-Volume Ratio| 1| 10.2891| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11189| 1/1.00| 10| | 1| 1972| 1/5.67| 8.41001| | 2| 394| 1/5.01| 7.37481| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 8.08979 m^2. Area projection in the x-plane = 0.572014 m^2, y-plane = 0.261888 m^2, z-plane = 3.84035 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380358 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.8602e-18 m, z-direction = -0.0467106 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.9058e-01| -0.788239| 1.511706| 1.187262| 4.680867| -1.151636| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.9486e-01| -1.114115| 1.416686| 1.030318| 4.340813| -0.880779| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.9775e-01| -1.184774| 1.271379| 0.880364| 4.266950| -0.265222| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.18477| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelastic_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |CSV file |surface_flow_aeroelastic_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary |flow_aeroelastic_Iterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelastic_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Ribs_and_Spars, index = 1 Name = Skin, index = 2 Name = Rib_Root, index = 3 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 746 Number of elements = 898 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 120 Elemental Quad4 = 778 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - Rib_Root Property name - Ribs_and_Spars Property name - Skin Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureAero No "groupName" specified for Load tuple pressureAero, going to use load name Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 3.096416e+09, tgt = 3.096416e+09, diff = 7.733565e+01 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 3.009946e+09, tgt = 3.009946e+09, diff = 6.083825e+01 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 4.109924e+07, tgt = 4.109924e+07, diff = 1.668003e+00 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 330 (total = 330) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 330 (total = 660) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 30 (total = 690) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Writing SU2 data transfer files Writing SU2 Motion File - aeroelastic_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 1.371946 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelastic_Iterative.dat. Surface file name: surface_flow_aeroelastic_Iterative. Volume file name: flow_aeroelastic_Iterative. Restart file name: restart_flow_aeroelastic_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 14880 TETRAHEDRON volume elements. There has been a re-orientation of 747 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 117384. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 405.677. Mean K: 3.64694. Standard deviation K: 20.0542. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 3.31568| 83.9604| | CV Face Area Aspect Ratio| 1.03244| 309.65| | CV Sub-Volume Ratio| 1| 74320.5| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11189| 1/1.00| 10| | 1| 1986| 1/5.63| 8.42986| | 2| 397| 1/5| 7.39348| +-------------------------------------------+ Finding max control volume width. Semi-span length = 12.4281 m. Wetted area = 1437.77 m^2. Area projection in the x-plane = 477.415 m^2, y-plane = 489.875 m^2, z-plane = 61.3163 m^2. Max. coordinate in the x-direction = 3.712 m, y-direction = 12.4281 m, z-direction = 36.4483 m. Min. coordinate in the x-direction = -13.6258 m, y-direction = -0.914733 m, z-direction = -76.7716 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 4.3848e-01| 2.942393| 5.901937| 6.281442| 8.411499| 0.200160| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 4.2505e-01| 3.381201| 5.896320| 6.239543| 8.911050| -2.031947| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 4.2051e-01| 3.486782| 5.971795| 6.207062| 8.952183| -0.068916| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 3.48678| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelastic_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |CSV file |surface_flow_aeroelastic_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary |flow_aeroelastic_Iterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelastic_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). +-----------------------------------------------------------------------+ Warning: there are 138 non-physical points in the solution. Warning: 3 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 1.665664e+09, tgt = 1.665662e+09, diff = 1.354985e+03 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 1.565774e+09, tgt = 1.565774e+09, diff = 2.317646e+02 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 1.026818e+07, tgt = 1.026821e+07, diff = 2.600373e+01 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 330 (total = 330) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 330 (total = 660) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 30 (total = 690) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Writing SU2 data transfer files Writing SU2 Motion File - aeroelastic_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. There has been a re-orientation of 14880 TETRAHEDRON volume elements. There has been a re-orientation of 747 TRIANGLE surface elements. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 117384. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 6.866808 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelastic_Iterative.dat. Surface file name: surface_flow_aeroelastic_Iterative. Volume file name: flow_aeroelastic_Iterative. Restart file name: restart_flow_aeroelastic_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 32647 TETRAHEDRON volume elements. There has been a re-orientation of 1729 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 8.42456e+10. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 17.3445. Mean K: 0.271106. Standard deviation K: 0.872252. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.158267| 81.1825| | CV Face Area Aspect Ratio| 1.08063| 64701.1| | CV Sub-Volume Ratio| 1| 1.29145e+06| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11189| 1/1.00| 10| | 1| 1993| 1/5.61| 8.43976| | 2| 418| 1/4.77| 7.52161| +-------------------------------------------+ Finding max control volume width. Semi-span length = 18.787 m. Wetted area = 2.03132e+06 m^2. Area projection in the x-plane = 676346 m^2, y-plane = 377082 m^2, z-plane = 21844.1 m^2. Max. coordinate in the x-direction = 28.6953 m, y-direction = 18.787 m, z-direction = 8014.26 m. Min. coordinate in the x-direction = -42.7756 m, y-direction = -585.579 m, z-direction = -0.0467106 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.5126e-01| 7.130954| 10.095885| 10.042605| 12.600060| -0.015751| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.5790e-01| 7.417851| 10.026146| 9.963905| 12.841572| -0.016442| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.6364e-01| 7.497783| 10.099626| 10.027466| 12.944525| -0.015842| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 7.49778| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelastic_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |CSV file |surface_flow_aeroelastic_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary |flow_aeroelastic_Iterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelastic_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). +-----------------------------------------------------------------------+ Warning: there are 423 non-physical points in the solution. Warning: 59 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 1.646540e+09, tgt = 1.646540e+09, diff = 3.843121e+01 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 1.350299e+09, tgt = 1.350299e+09, diff = 7.153354e+00 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 104 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 1.438119e+07, tgt = 1.438112e+07, diff = 7.043509e+01 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 330 (total = 330) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 330 (total = 660) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 30 (total = 690) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Writing SU2 data transfer files Writing SU2 Motion File - aeroelastic_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. There has been a re-orientation of 32647 TETRAHEDRON volume elements. There has been a re-orientation of 1729 TRIANGLE surface elements. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 8.42456e+10. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 41.218099 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelastic_Iterative.dat. Surface file name: surface_flow_aeroelastic_Iterative. Volume file name: flow_aeroelastic_Iterative. Restart file name: restart_flow_aeroelastic_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 11189 grid points. 57882 volume elements. 3 surface markers. 3444 boundary elements in index 0 (Marker = BC_1). 1831 boundary elements in index 1 (Marker = BC_2). 195 boundary elements in index 2 (Marker = BC_3). 57882 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 33140 TETRAHEDRON volume elements. There has been a re-orientation of 2846 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 8.586e+13. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 12.5581. Mean K: 0.244836. Standard deviation K: 0.957256. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.154366| 80.0576| | CV Face Area Aspect Ratio| 1.50305| 2.99554e+08| | CV Sub-Volume Ratio| 1| 2.02824e+10| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11189| 1/1.00| 10| | 1| 1994| 1/5.61| 8.44117| | 2| 416| 1/4.79| 7.5096| +-------------------------------------------+ Finding max control volume width. Semi-span length = 121.933 m. Wetted area = 94584.5 m^2. Area projection in the x-plane = 44339 m^2, y-plane = 12667.1 m^2, z-plane = 998.251 m^2. Max. coordinate in the x-direction = 14.9317 m, y-direction = 121.933 m, z-direction = 31.3447 m. Min. coordinate in the x-direction = -41.4907 m, y-direction = -1.80731 m, z-direction = -1545.06 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.9801e-01| 8.948112| 11.914968| 11.851545| 14.417218| -0.122706| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 4.1112e-01| 9.294124| 11.889659| 11.826417| 14.715823| -0.129444| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 4.0890e-01| 9.347261| 11.933459| 11.877931| 14.801676| -0.155743| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 9.34726| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelastic_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |CSV file |surface_flow_aeroelastic_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary |flow_aeroelastic_Iterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelastic_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). +-----------------------------------------------------------------------+ Warning: there are 677 non-physical points in the solution. Warning: 58 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 real 1m42.669s user 1m41.544s sys 0m7.693s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelastic_Iterative_SU2_and_Astros.py passed (as expected) ================================================= ================================================= + echo 'aeroelasticSimple_Temperature_SU2_and_TACS.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt aeroelasticSimple_Temperature_SU2_and_TACS.py test; + python -u aeroelasticSimple_Temperature_SU2_and_TACS.py -outLevel=0 -noPlotData + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Running PreAnalysis ...... su2 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 1 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 9 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 12 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 4 5 EGADS : 2 Yes 0 0 1 0 1 1 3 5 6 EGADS : 3 Yes 0 0 1 0 1 1 2 4 6 7 8 EGADS : 4 Yes 0 0 1 0 1 1 3 5 6 EGADS : 5 Yes 0 0 1 0 1 1 2 4 6 EGADS : 6 Yes 0 0 1 0 1 2 3 4 5 EGADS : 7 Yes 0 0 1 0 1 3 8 9 EGADS : 8 Yes 0 0 1 0 1 3 7 9 EGADS : 9 Yes 0 0 1 0 1 7 8 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 1 2 -3 -4 EGADS : 2 5 6 -7 -1 EGADS : 3 -2 7 9 -8 -10 -11 EGADS : 4 -12 3 8 -13 EGADS : 5 4 12 -14 -5 EGADS : 6 -6 14 13 -9 EGADS : 7 15 10 -17 -16 EGADS : 8 17 11 -15 -18 EGADS : 9 16 18 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 4 EGADS : 4 5 EGADS : 5 6 EGADS : 6 7 EGADS : 7 8 EGADS : 8 9 EGADS : 9 10 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes 1 2 -3 -4 EGADS : 2 Yes 5 6 -7 -1 EGADS : 3 Yes -2 7 9 -8 EGADS : 4 Yes -10 -11 EGADS : 5 Yes -12 3 8 -13 EGADS : 6 Yes 4 12 -14 -5 EGADS : 7 Yes -6 14 13 -9 EGADS : 8 Yes 15 10 -17 -16 EGADS : 9 Yes 17 11 -15 -18 EGADS : 10 Yes 16 18 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 2 1 1 1 2 EGADS : 2 0 Yes 1 3 1 1 3 EGADS : 3 0 Yes 4 3 1 1 4 EGADS : 4 0 Yes 2 4 1 1 5 EGADS : 5 0 Yes 2 5 1 2 5 EGADS : 6 0 Yes 5 6 1 2 6 EGADS : 7 0 Yes 1 6 1 2 3 EGADS : 8 0 Yes 3 7 1 3 4 EGADS : 9 0 Yes 6 7 1 3 6 EGADS : 10 0 Yes 8 9 1 3 7 EGADS : 11 0 Yes 9 8 1 3 8 EGADS : 12 0 Yes 4 10 1 4 5 EGADS : 13 0 Yes 10 7 1 4 6 EGADS : 14 0 Yes 5 10 1 5 6 EGADS : 15 0 Yes 11 8 1 7 8 EGADS : 16 0 Yes 11 12 1 7 9 EGADS : 17 0 Yes 12 9 1 7 8 EGADS : 18 0 Yes 12 11 1 8 9 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 0 0 0 EGADS : 2 Yes 0 40 0 EGADS : 3 Yes 0 0 20 EGADS : 4 Yes 0 40 20 EGADS : 5 Yes 20 40 0 EGADS : 6 Yes 20 0 0 EGADS : 7 Yes 20 0 20 EGADS : 8 Yes 1.61374306 0 0 EGADS : 9 Yes 0 0 0 EGADS : 10 Yes 20 40 20 EGADS : 11 Yes 2.53650745 3.87298335 0.334116517 EGADS : 12 Yes 1.57194608 3.87298335 0.249728332 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 40 AFLR4 : Min Bounding Box Length = 40 AFLR4 : Max Ref Bounding Box Length = 40 AFLR4 : Min Ref Bounding Box Length = 40 AFLR4 : Reference Length = 1.61374 AFLR4 : BL Thickness = 0 AFLR4 : Abs Min Surf Spacing = 0.00403436 AFLR4 : Min Surf Spacing = 0.161374 AFLR4 : Max Surf Spacing = 1.21031 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Nodes, Trias,Quads= 1293 2452 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Nodes, Trias,Quads= 1298 2462 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 3418 6687 0 AFLR4 : Nodes, Trias,Quads= 3008 5867 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1315 2496 0 AFLR4 : Nodes, Trias,Quads= 1297 2460 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Nodes, Trias,Quads= 1298 2462 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1319 2504 0 AFLR4 : Nodes, Trias,Quads= 1294 2454 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 200 344 0 AFLR4 : Nodes, Trias,Quads= 160 264 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 193 330 0 AFLR4 : Nodes, Trias,Quads= 155 254 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 17 21 0 AFLR4 : Nodes, Trias,Quads= 11 9 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 9344 18684 928 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 9344 18684 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1335 2536 0 AFLR4 : Nodes, Trias,Quads= 1317 2500 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1337 2540 0 AFLR4 : Nodes, Trias,Quads= 1320 2506 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 3787 7420 0 AFLR4 : Nodes, Trias,Quads= 2943 5732 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1341 2548 0 AFLR4 : Nodes, Trias,Quads= 1321 2508 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 1337 2540 0 AFLR4 : Nodes, Trias,Quads= 1320 2506 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1342 2550 0 AFLR4 : Nodes, Trias,Quads= 1318 2502 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 233 404 0 AFLR4 : Nodes, Trias,Quads= 210 358 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 224 386 0 AFLR4 : Nodes, Trias,Quads= 196 330 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 18 22 0 AFLR4 : Nodes, Trias,Quads= 12 10 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 9478 18952 946 OVERALL : CPU Time = 0.316 seconds Body 1 (of 1) Number of nodes = 9478 Number of elements = 18952 Number of triangle elements = 18952 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 9478 Total number of elements = 18952 Total number of triangle elements = 18952 Total number of quadrilateral elements = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 61788 Number of elements = 355965 Number of triangles = 18952 Number of quadrilatarals = 0 Number of tetrahedrals = 337013 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Skin Boundary condition name - SymmPlane Done getting CFD boundary conditions Info: No recognized data transfer names found. Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Temperature_SM.dat. Surface file name: surface_flow_aeroelasticSimple_Temperature_SM. Volume file name: flow_aeroelasticSimple_Temperature_SM. Restart file name: restart_flow_aeroelasticSimple_Temperature_SM.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 61788 grid points. 337013 volume elements. 3 surface markers. 12522 boundary elements in index 0 (Marker = BC_1). 5732 boundary elements in index 1 (Marker = BC_2). 698 boundary elements in index 2 (Marker = BC_3). 337013 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 63999.5. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 83.4538. Mean K: 0.863308. Standard deviation K: 5.00657. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 54.7348| 86.7581| | CV Face Area Aspect Ratio| 1.06698| 21.5651| | CV Sub-Volume Ratio| 1| 6.22786| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 61788| 1/1.00| 10| | 1| 10504| 1/5.88| 8.3095| | 2| 1841| 1/5.71| 6.97535| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 9.2451 m^2. Area projection in the x-plane = 0.651846 m^2, y-plane = 0.30478 m^2, z-plane = 4.4157 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.38 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.86329e-18 m, z-direction = -0.0467611 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 2.1617e+00| -1.361370| 0.918961| 0.580745| 4.107735| -0.945745| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.1752e+00| -1.753698| 0.759192| 0.409261| 3.702741| -0.508573| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.1425e+00| -1.769228| 0.570930| 0.229342| 3.687595| 1.615844| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.76923| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Temperature_SM.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Temperature_SM.dat). |CSV file |surface_flow_aeroelasticSimple_Temperature_SM.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Temperature_SM.dat). |Tecplot binary |flow_aeroelasticSimple_Temperature_SM.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Temperature_SM.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Temperature_SM.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Temperature_SM.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... tacs Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 12 Number of elements = 12 Number of triangle elements = 4 Number of quadrilateral elements = 8 ---------------------------- Total number of nodes = 12 Total number of elements = 12 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 12 Number of elements = 12 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4 Elemental Quad4 = 8 Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Rib_Root Property name - Skin Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - Skin No "groupName" specified for Load tuple Skin, going to use load name Done getting FEA loads Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 12 Number of elements = 12 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4 Elemental Quad4 = 8 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Temperature_SM.csv Number of variables = 16 Number of data points = 361 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Temperature' Rank 0: src = 1.497486e+03, tgt = 1.497486e+03, diff = 4.587847e-06 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 12 Number of elements = 12 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4 Elemental Quad4 = 8 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Temperature_SM.csv Number of variables = 16 Number of data points = 361 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Temperature' Rank 0: src = 1.453112e+03, tgt = 1.453112e+03, diff = 4.579270e-06 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 12 Number of elements = 12 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4 Elemental Quad4 = 8 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Temperature_SM.csv Number of variables = 16 Number of data points = 361 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Temperature' Rank 0: src = 2.097348e+01, tgt = 2.097348e+01, diff = 3.279155e-12 Extracting external thermal loads from data transfer.... TransferName = Skin_Top Number of Nodes = 9 (total = 9) Extracting external thermal loads from data transfer.... TransferName = Skin_Bottom Number of Nodes = 9 (total = 18) Extracting external thermal loads from data transfer.... TransferName = Skin_Tip Number of Nodes = 4 (total = 16) Writing Nastran grid and connectivity file (in free field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing TACS instruction file.... Writing analysis cards Writing load ADD cards Writing constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Running PostAnalysis ...... tacs real 0m25.104s user 0m23.101s sys 0m2.411s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelasticSimple_Temperature_SU2_and_TACS.py passed (as expected) ================================================= Running.... CORSAIRLITE PyTests ================================================= + echo 'gp.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt gp.py test; + python -u gp.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Objective --------- 0.00713 dimensionless Variables --------- x : 3.00000 [-] The X variable y : 81.00008 [-] The Y variable z : 0.19245 [-] The Z variable Sensitivities ------------- No Constants in the Formulation Solve Report ------------ Solve Method : Geometric Program Classification : Convex Solver : cvxopt real 0m9.897s user 0m2.095s sys 0m0.380s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case gp.py passed (as expected) ================================================= ================================================= + echo 'qp.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt qp.py test; + python -u qp.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Objective --------- -21.56250 dimensionless Variables --------- x : 1.62500 [-] The X variable y : 1.37500 [-] The Y variable Constants --------- c : 3 [-] A constant c2 : 2 [-] A constant Sensitivities ------------- c : + 0.46957 A constant c2 : - 0.22338 A constant Solve Report ------------ Solve Method : Quadratic Program Classification : Convex Solver : cvxopt real 0m2.221s user 0m2.179s sys 0m0.261s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case qp.py passed (as expected) ================================================= ================================================= + echo 'sp.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt sp.py test; + python -u sp.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Objective --------- 0.45721 dimensionless Variables --------- x : 2.56155 [-] The X variable y : 6.56155 [-] The Y variable z : 1.17116 [-] The Z variable Constants --------- c : 2 [-] A constant Sensitivities ------------- Sensitivities not computed Solve Report ------------ Solve Method : Signomial Program--Standard Classification : Iterative Solver : cvxopt Number of Iterations : 3 Termination Status : Converged, relative error (3.15e-04) is less than specified tolerance (1.00e-03) real 0m2.258s user 0m2.109s sys 0m0.283s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case sp.py passed (as expected) ================================================= ================================================= + echo 'boydBox.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt boydBox.py test; + python -u boydBox.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Objective --------- 0.00520 1 / meter ** 3 Variables --------- d : 11.26658 meter The Z variable h : 2.92246 meter The Y variable w : 5.84486 meter The X variable Constants --------- Aflr : 1000 meter ** 2 Area of floor Awall : 100 meter ** 2 Area of wall alpha : 0.50000 [-] Aspect Ratio Constraint beta : 2 [-] Aspect Ratio Constraint delta : 2 [-] Aspect Ratio Constraint gamma : 0.50000 [-] Aspect Ratio Constraint Sensitivities ------------- Sensitivities not computed Solve Report ------------ Solve Method : Geometric Program Classification : Convex Solver : cvxopt real 0m1.875s user 0m1.823s sys 0m0.259s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case boydBox.py passed (as expected) ================================================= ================================================= + echo 'hoburg_gp.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt hoburg_gp.py test; + python -u hoburg_gp.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Objective --------- 5905.58568 newton Variables --------- AR : 20.36983 [-] aspect ratio C_D_0 : 0.01271 [-] Drag Coefficient, segment 0 C_D_1 : 0.01273 [-] Drag Coefficient, segment 1 C_D_2 : 0.00778 [-] Drag Coefficient, segment 2 C_Dfuse_0 : 0.00180 [-] Fuselage Drag Coefficient, segment 0 C_Dfuse_1 : 0.00180 [-] Fuselage Drag Coefficient, segment 1 C_Dfuse_2 : 0.00180 [-] Fuselage Drag Coefficient, segment 2 C_Di_0 : 0.00542 [-] Induced Drag Coefficient, segment 0 C_Di_1 : 0.00542 [-] Induced Drag Coefficient, segment 1 C_Di_2 : 0.00023 [-] Induced Drag Coefficient, segment 2 C_Dp_0 : 0.00549 [-] Wing Profile Drag Coefficient, segment 0 C_Dp_1 : 0.00551 [-] Wing Profile Drag Coefficient, segment 1 C_Dp_2 : 0.00575 [-] Wing Profile Drag Coefficient, segment 2 C_L_0 : 0.57420 [-] Lift Coefficient, segment 0 C_L_1 : 0.57421 [-] Lift Coefficient, segment 1 C_L_2 : 0.11881 [-] Lift Coefficient, segment 2 I_cap_bar : 0.00002 [-] Area moment of inertia of cap on 2D cross section, normalized by chord^4 M_r_bar : 36139.20785 newton Root Bending unit per unit chord P_max : 1185884.98442 watt Maximum Engine Power R : 4999.98983 kilometer Single Segment range Re_0 : 4232645.50367 [-] Reynolds Number, segment 0 Re_1 : 4051247.93913 [-] Reynolds Number, segment 1 Re_2 : 9305153.26607 [-] Reynolds Number, segment 2 S : 27.73109 meter ** 2 total wing area T_0 : 746.21338 newton Thrust, segment 0 T_1 : 684.51827 newton Thrust, segment 1 T_2 : 2208.51611 newton Thrust, segment 2 V_0 : 68.23357 meter / second Velocity, segment 0 V_1 : 65.30930 meter / second Velocity, segment 1 V_2 : 150.00638 meter / second Velocity, segment 2 V_stall : 37.99896 meter / second stall speed W_0 : 33698.97702 newton Weight, segment 0 W_1 : 30873.13301 newton Weight, segment 1 W_2 : 33698.96566 newton Weight, segment 2 W_MTO : 36788.13387 newton Maximum Takeoff Weight W_cap : 4091.65066 newton Weight of Wing Spar Cap W_eng : 2806.10727 newton Engine Weight W_fuel_out : 3079.86524 newton Weight of fuel, outbound W_fuel_ret : 2825.71897 newton Weight of fuel, return W_pay : 4905.15902 newton Payload Weight W_tilde : 22409.98513 newton Dry Weight, no wing W_web : 139.91823 newton Weight of Wing Spar Shear Web W_wing : 8462.91404 newton wing weight W_zfw : 30872.92436 newton Zero Fuel Weight eta_0_0 : 0.26999 [-] Overall Efficiency, segment 0 eta_0_1 : 0.26996 [-] Overall Efficiency, segment 1 eta_0_2 : 0.27945 [-] Overall Efficiency, segment 2 eta_i_0 : 0.90752 [-] Inviscid Propeller Efficiency, segment 0 eta_i_1 : 0.90742 [-] Inviscid Propeller Efficiency, segment 1 eta_i_2 : 0.93932 [-] Inviscid Propeller Efficiency, segment 2 eta_prop_0 : 0.77139 [-] Propeller Efficiency, segment 0 eta_prop_1 : 0.77131 [-] Propeller Efficiency, segment 1 eta_prop_2 : 0.79842 [-] Propeller Efficiency, segment 2 nu : 0.78603 [-] Placeholder, (1+lam_w+lam_w**2)/(1+lam_w)**2 p : 1.90003 [-] Dummy Variable (1+2*lam_w) q : 1.45002 [-] Dummy Variable (1+lam_w) t_cap_bar : 0.00456 [-] Spar cap thickness per unit chord t_web_bar : 0.00069 [-] Spar web thickness per unit chord tau : 0.15000 [-] airfoil thickness to chord ratio z_bre_0 : 0.08745 [-] Breguet Range Factor, segment 0 z_bre_1 : 0.08758 [-] Breguet Range Factor, segment 1 Constants --------- A_prop : 0.78500 meter ** 2 Disk area of propeller CDA0 : 0.05000 meter ** 2 fuselage drag area C_Lmax : 1.50000 [-] max CL with flaps down N_lift : 6 [-] Ultimate Load Factor W_fixed : 14700 newton fixed weight e : 0.95000 [-] Oswald efficiency factor eta_eng : 0.35000 [-] Engine Efficiency eta_v : 0.85000 [-] Propeller Viscous Efficiency f_wadd : 2 [-] Added Weight Fraction g : 9.81000 meter / second ** 2 Gravitational constant h_fuel : 46000000 joule / kilogram Fuel Specific energy density k_ew : 0.03720 newton / watt ** 0.803 Constant for engine weight mu : 0.00002 kilogram / meter / second viscosity of air r_h : 0.75000 [-] Ratio of height at rear spar to maximum wing height rho : 0.90912 kilogram / meter ** 3 density of air rho_SL : 1.22500 kilogram / meter ** 3 density of air, sea level rho_cap : 2700 kilogram / meter ** 3 Density of wing cap material (aluminum) rho_web : 2700 kilogram / meter ** 3 Density of wing web material (aluminum) sigma_max : 310 megapascal Allowable tensile stress of aluminum sigma_max_shear : 167 megapascal Allowable shear stress of aluminum w_bar : 0.50000 [-] Ratio of spar box width to chord length Sensitivities ------------- Sensitivities not computed Solve Report ------------ Solve Method : Geometric Program Classification : Convex Solver : cvxopt real 0m15.830s user 0m15.195s sys 0m0.784s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case hoburg_gp.py passed (as expected) ================================================= ================================================= + echo 'hoburg_blackbox.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt hoburg_blackbox.py test; + python -u hoburg_blackbox.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Objective --------- 5905.2294 newton Variables --------- AR : 20.3737 [-] aspect ratio C_D_0 : 0.0127 [-] Drag Coefficient, segment 0 C_D_1 : 0.0127 [-] Drag Coefficient, segment 1 C_D_2 : 0.0078 [-] Drag Coefficient, segment 2 C_Dfuse_0 : 0.0018 [-] Fuselage Drag Coefficient, segment 0 C_Dfuse_1 : 0.0018 [-] Fuselage Drag Coefficient, segment 1 C_Dfuse_2 : 0.0018 [-] Fuselage Drag Coefficient, segment 2 C_Di_0 : 0.0054 [-] Induced Drag Coefficient, segment 0 C_Di_1 : 0.0054 [-] Induced Drag Coefficient, segment 1 C_Di_2 : 0.0002 [-] Induced Drag Coefficient, segment 2 C_Dp_0 : 0.0055 [-] Wing Profile Drag Coefficient, segment 0 C_Dp_1 : 0.0055 [-] Wing Profile Drag Coefficient, segment 1 C_Dp_2 : 0.0057 [-] Wing Profile Drag Coefficient, segment 2 C_L_0 : 0.5743 [-] Lift Coefficient, segment 0 C_L_1 : 0.5743 [-] Lift Coefficient, segment 1 C_L_2 : 0.1189 [-] Lift Coefficient, segment 2 I_cap_bar : 0.0000 [-] Area moment of inertia of cap on 2D cross section, normalized by chord^4 M_r_bar : 36141.5015 newton Root Bending unit per unit chord P_max : 1184357.7688 watt Maximum Engine Power R : 5000.0000 kilometer Single Segment range Re_0 : 4231748.4656 [-] Reynolds Number, segment 0 Re_1 : 4050340.4364 [-] Reynolds Number, segment 1 Re_2 : 9301869.2065 [-] Reynolds Number, segment 2 S : 27.7189 meter ** 2 total wing area T_0 : 746.1648 newton Thrust, segment 0 T_1 : 684.5072 newton Thrust, segment 1 T_2 : 2206.5587 newton Thrust, segment 2 V_0 : 68.2403 meter / second Velocity, segment 0 V_1 : 65.3149 meter / second Velocity, segment 1 V_2 : 150.0000 meter / second Velocity, segment 2 V_stall : 38.0000 meter / second stall speed W_0 : 33694.3546 newton Weight, segment 0 W_1 : 30868.7209 newton Weight, segment 1 W_2 : 33694.3546 newton Weight, segment 2 W_MTO : 36773.9503 newton Maximum Takeoff Weight W_cap : 4091.0280 newton Weight of Wing Spar Cap W_eng : 2802.5264 newton Engine Weight W_fuel_out : 3079.5957 newton Weight of fuel, outbound W_fuel_ret : 2825.6337 newton Weight of fuel, return W_pay : 4905.0000 newton Payload Weight W_tilde : 22407.5264 newton Dry Weight, no wing W_web : 139.5692 newton Weight of Wing Spar Shear Web W_wing : 8461.1945 newton wing weight W_zfw : 30868.7209 newton Zero Fuel Weight eta_0_0 : 0.2700 [-] Overall Efficiency, segment 0 eta_0_1 : 0.2700 [-] Overall Efficiency, segment 1 eta_0_2 : 0.2795 [-] Overall Efficiency, segment 2 eta_i_0 : 0.9075 [-] Inviscid Propeller Efficiency, segment 0 eta_i_1 : 0.9074 [-] Inviscid Propeller Efficiency, segment 1 eta_i_2 : 0.9394 [-] Inviscid Propeller Efficiency, segment 2 eta_prop_0 : 0.7714 [-] Propeller Efficiency, segment 0 eta_prop_1 : 0.7713 [-] Propeller Efficiency, segment 1 eta_prop_2 : 0.7985 [-] Propeller Efficiency, segment 2 nu : 0.7860 [-] Placeholder, (1+lam_w+lam_w**2)/(1+lam_w)**2 p : 1.9000 [-] Dummy Variable (1+2*lam_w) q : 1.4500 [-] Dummy Variable (1+lam_w) t_cap_bar : 0.0046 [-] Spar cap thickness per unit chord t_web_bar : 0.0007 [-] Spar web thickness per unit chord tau : 0.1500 [-] airfoil thickness to chord ratio z_bre_0 : 0.0875 [-] Breguet Range Factor, segment 0 z_bre_1 : 0.0876 [-] Breguet Range Factor, segment 1 Constants --------- A_prop : 0.7850 meter ** 2 Disk area of propeller CDA0 : 0.0500 meter ** 2 fuselage drag area C_Lmax : 1.5000 [-] max CL with flaps down N_lift : 6 [-] Ultimate Load Factor W_fixed : 14700 newton fixed weight e : 0.9500 [-] Oswald efficiency factor eta_eng : 0.3500 [-] Engine Efficiency eta_v : 0.8500 [-] Propeller Viscous Efficiency f_wadd : 2 [-] Added Weight Fraction g : 9.8100 meter / second ** 2 Gravitational constant h_fuel : 46000000 joule / kilogram Fuel Specific energy density k_ew : 0.0372 newton / watt ** 0.803 Constant for engine weight mu : 0.0000 kilogram / meter / second viscosity of air r_h : 0.7500 [-] Ratio of height at rear spar to maximum wing height rho : 0.9091 kilogram / meter ** 3 density of air rho_SL : 1.2250 kilogram / meter ** 3 density of air, sea level rho_cap : 2700 kilogram / meter ** 3 Density of wing cap material (aluminum) rho_web : 2700 kilogram / meter ** 3 Density of wing web material (aluminum) sigma_max : 310 megapascal Ultimate tensile stress of aluminum sigma_max_shear : 167 megapascal Ultimate shear stress of aluminum w_bar : 0.5000 [-] Ratio of spar box width to chord length Sensitivities ------------- Sensitivities not currently implemented for optimization type Logspace Sequential Quadratic Program Solve Report ------------ Solve Method : Logspace Sequential Quadratic Program Classification : Iterative Solver : cvxopt Number of Iterations : 7 Termination Status : Converged, gradient of Lagrangian (9.638917e-07) within tolerance (1.000000e-06) Messages -------- 1. Wolfe Condition 1 failed at iteration 5 (Step 5). Watchdog counter is 1 2. Wolfe Condition 1 failed at iteration 6 (Step 6). Watchdog counter is 2 real 1m3.235s user 1m2.017s sys 0m0.951s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case hoburg_blackbox.py passed (as expected) ================================================= ================================================= + echo 'pyCAPS/sizeWing.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt pyCAPS/sizeWing.py test; + python -u pyCAPS/sizeWing.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt nrock 2 Objective --------- 0.075 dimensionless Variables --------- AR : 10.000 [-] Wing aspect ratio CD : 0.075 [-] Drag Coefficient CL : 0.999 [-] Lift Coefficient S : 2.642 meter ** 2 Wing area V : 2.722 meter / second Airspeed W : 11.979 newton Aircraft weight Wwing : 1.598 newton Wing weight Constants --------- ARmax : 10 [-] Max AR CD0 : 0.040 [-] Profile drag CLmax : 1 [-] Max CL E0 : 10 joule Maximum elastic potential energy in rubber band Wfixed : 0.100 newton Weight of fixed components Wrock : 2 newton Weight of each rock e : 0.900 [-] Oswawld efficiency factor g : 9.810 meter / second ** 2 Gravitational constant nrock : 2 [-] Number of rocks to carry rho : 1.225 kilogram / meter ** 3 Density of air rho_wing : 1 kilogram / meter ** 3 Weight density of wing tau : 0.120 [-] Airfoil thickness as t/c Sensitivities ------------- Sensitivities not computed Solve Report ------------ Solve Method : Geometric Program Classification : Convex Solver : cvxopt Optimized L/D: 13.267784561972134 EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! real 0m2.965s user 0m2.782s sys 0m0.371s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case pyCAPS/sizeWing.py passed (as expected) ================================================= avl: /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/avl ================================================= + echo 'pyCAPS/optTaperAvl.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt pyCAPS/optTaperAvl.py test; + python -u pyCAPS/optTaperAvl.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Objective --------- 1.00805 dimensionless Variables --------- e : 0.99202 [-] Oswald efficiency factor lam : 0.39881 [-] Wing taper ratio Sensitivities ------------- Sensitivities not available for optimizations of type Sequential Log Convex Program Solve Report ------------ Solve Method : Sequential Log Convex Program Classification : Iterative Solver : cvxopt Number of Iterations : 6 Termination Status : Converged, gradient of Lagrangian (5.888798e-08) within tolerance (1.000000e-06) Messages -------- 1. Wolfe Condition 1 failed at iteration 5 (Step 5). Watchdog counter is 1 real 0m10.814s user 0m6.997s sys 0m3.445s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case pyCAPS/optTaperAvl.py passed (as expected) ================================================= ================================================= + echo 'pyCAPS/optWingAvl.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt pyCAPS/optWingAvl.py test; + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt + python -u pyCAPS/optWingAvl.py -outLevel=0 nrock 2 Starting iteration 0 at 0.4478 seconds AR : 9.0 dimensionless CD : 0.1 dimensionless CL : 1.0 dimensionless S : 1.0 meter ** 2 V : 1.0 meter / second W : 10.0 newton Wwing : 0.1 newton e : 1.0 dimensionless lam : 0.3 dimensionless AVL run case - lam, AR: 0.3 9.0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) y: 0.9905504143712881 dimensionless dydx: [, ] Calling cvxopt.solvers.cp at 2.5927 seconds Got sol from cvxopt at 2.6195 seconds status optimal x [ 1.05e-01] [-3.26e-01] [-1.49e-11] [-4.10e-01] [ 1.28e+00] [-6.40e-01] [ 7.00e-01] [-1.08e-02] [ 5.73e-03] [-3.20e-16] [ 3.50e-16] [ 1.56e-16] [ 5.20e-16] [ 2.70e-16] [ 4.16e-27] [ 3.37e-16] [ 2.07e-23] y [-6.40e-01] [ 7.00e-01] [ 3.11e-01] znl [ 6.74e-01] [ 4.14e-08] zl [ 1.04e+00] [ 5.41e-01] [ 8.31e-12] snl [ 8.55e-11] [ 2.03e-01] sl [ 1.49e-11] [ 4.30e-10] [ 8.74e-01] gap 8.743959706206368e-09 relative gap 7.194197617463699e-09 primal objective -1.2154183372695613 dual objective -1.2154183416835473 primal slack 1.3843122277350236e-11 dual slack 8.310943825859287e-12 primal infeasibility 1.1390346865902829e-09 dual infeasibility 2.382340215936626e-11 AVL run case - lam, AR: 0.3017253411785192 9.999999995701312 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) y: 0.9892210301573763 dimensionless dydx: [, ] logspace stuff at 4.7388 seconds Starting iteration 1 at 4.7811 seconds AR : 9.999999995701312 dimensionless CD : 0.07217671497330203 dimensionless CL : 0.9999999999851361 dimensionless S : 0.6639217992634345 meter ** 2 V : 3.600068783658014 meter / second W : 5.270412635736404 newton Wwing : 0.20138431695627712 newton e : 0.9892553874048055 dimensionless lam : 0.3017253411785192 dimensionless Calling cvxopt.solvers.cp at 4.7999 seconds Got sol from cvxopt at 4.8342 seconds status optimal x [ 3.90e-10] [-5.94e-05] [-1.96e-07] [ 1.14e-08] [ 7.38e-08] [-3.68e-08] [ 1.70e-08] [ 1.33e-04] [ 8.64e-03] [ 6.35e-21] [-6.95e-21] [ 2.23e-16] [ 5.42e-17] [ 2.20e-16] [ 1.27e-26] [ 5.00e-16] [ 6.63e-26] y [ 1.27e-05] [-1.39e-05] [ 4.46e-01] znl [ 1.00e+00] [ 1.33e-10] zl [ 1.08e-01] [ 4.39e-01] [ 2.53e-11] snl [ 2.06e-11] [ 2.03e-01] sl [ 1.96e-07] [ 4.02e-11] [ 8.74e-01] gap 2.1363031594082996e-08 relative gap 8.126967446318895e-09 primal objective -2.628659673511965 dual objective -2.6286596843378565 primal slack 2.057784648141205e-11 dual slack 2.5305040678747188e-11 primal infeasibility 3.0858031730676883e-09 dual infeasibility 3.1339132207348104e-09 AVL run case - lam, AR: 0.3043446483574454 9.99999999959832 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) y: 0.9893844569300864 dimensionless dydx: [, ] logspace stuff at 6.5114 seconds Starting iteration 2 at 6.5689 seconds AR : 9.99999999959832 dimensionless CD : 0.07217242517886534 dimensionless CL : 0.9999998041107226 dimensionless S : 0.6639218068635588 meter ** 2 V : 3.6000690493939635 meter / second W : 5.270412441791246 newton Wwing : 0.20138432037500312 newton e : 0.989386895901959 dimensionless lam : 0.3043446483574454 dimensionless Calling cvxopt.solvers.cp at 6.5857 seconds Got sol from cvxopt at 6.6143 seconds status optimal x [ 7.75e-13] [-3.52e-04] [ 4.29e-09] [-2.11e-10] [-1.42e-09] [ 1.25e-09] [-3.17e-10] [ 7.91e-04] [ 4.20e-02] [ 7.26e-21] [-7.89e-21] [ 2.23e-16] [ 5.45e-17] [ 2.20e-16] [ 1.24e-26] [ 5.00e-16] [ 6.65e-26] y [ 1.45e-05] [-1.58e-05] [ 4.45e-01] znl [ 1.00e+00] [ 1.33e-10] zl [ 1.09e-01] [ 4.39e-01] [ 2.49e-11] snl [ 2.02e-11] [ 2.03e-01] sl [ 1.92e-07] [ 3.94e-11] [ 8.74e-01] gap 2.0979541929842845e-08 relative gap 7.980432611695012e-09 primal objective -2.628872763000109 dual objective -2.628872773631958 primal slack 2.02261955200119e-11 dual slack 2.487027023449014e-11 primal infeasibility 3.030673451220543e-09 dual infeasibility 3.0769324710021364e-09 AVL run case - lam, AR: 0.3174093513141959 9.999999999606068 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) y: 0.9901147289475967 dimensionless dydx: [, ] logspace stuff at 8.4138 seconds Starting iteration 3 at 8.4792 seconds AR : 9.999999999606068 dimensionless CD : 0.0721469915733377 dimensionless CL : 0.9999998084033913 dimensionless S : 0.6639218067235316 meter ** 2 V : 3.6000690442960233 meter / second W : 5.270412448377285 newton Wwing : 0.20138432031121437 newton e : 0.9901696737886684 dimensionless lam : 0.3174093513141959 dimensionless Calling cvxopt.solvers.cp at 8.4963 seconds Got sol from cvxopt at 8.5348 seconds status optimal x [ 2.14e-12] [-1.28e-03] [ 1.17e-08] [-5.10e-10] [-3.51e-09] [ 4.16e-09] [-7.67e-10] [ 2.88e-03] [ 1.81e-01] [-4.10e-21] [ 4.49e-21] [ 2.23e-16] [ 5.51e-17] [ 2.20e-16] [ 1.18e-26] [ 5.00e-16] [ 6.61e-26] y [-8.19e-06] [ 8.98e-06] [ 4.45e-01] znl [ 1.00e+00] [ 1.32e-10] zl [ 1.10e-01] [ 4.40e-01] [ 2.37e-11] snl [ 1.92e-11] [ 2.03e-01] sl [ 1.80e-07] [ 3.73e-11] [ 8.74e-01] gap 1.9913348950487102e-08 relative gap 7.572537674639902e-09 primal objective -2.6296797462198227 dual objective -2.629679756312197 primal slack 1.9233234441874093e-11 dual slack 2.3654666052959533e-11 primal infeasibility 2.8765759486725376e-09 dual infeasibility 2.9202708054711625e-09 AVL run case - lam, AR: 0.3802990571782025 9.999999999627487 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) y: 0.9919295458295875 dimensionless dydx: [, ] logspace stuff at 10.2780 seconds Starting iteration 4 at 10.3333 seconds AR : 9.999999999627487 dimensionless CD : 0.07205440311148241 dimensionless CL : 0.9999998201037487 dimensionless S : 0.6639218063847038 meter ** 2 V : 3.600069031643119 meter / second W : 5.270412470306208 newton Wwing : 0.20138432015683602 newton e : 0.9930297814905515 dimensionless lam : 0.3802990571782025 dimensionless Calling cvxopt.solvers.cp at 10.3482 seconds Got sol from cvxopt at 10.3837 seconds status optimal x [-1.57e-12] [ 4.08e-04] [-8.59e-09] [ 5.53e-10] [ 3.53e-09] [-9.72e-10] [ 8.30e-10] [-9.18e-04] [ 5.19e-02] [-2.12e-20] [ 2.32e-20] [ 2.24e-16] [ 5.46e-17] [ 2.20e-16] [ 1.23e-26] [ 5.00e-16] [ 6.59e-26] y [-4.25e-05] [ 4.64e-05] [ 4.47e-01] znl [ 1.00e+00] [ 1.32e-10] zl [ 1.09e-01] [ 4.39e-01] [ 2.45e-11] snl [ 1.99e-11] [ 2.03e-01] sl [ 1.88e-07] [ 3.88e-11] [ 8.74e-01] gap 2.0688403479273492e-08 relative gap 7.866667127599179e-09 primal objective -2.629881644119772 dual objective -2.629881654604474 primal slack 1.9944303018455954e-11 dual slack 2.4539201182166233e-11 primal infeasibility 2.9853821718634855e-09 dual infeasibility 3.0364291201811334e-09 AVL run case - lam, AR: 0.40055731597956656 9.999999999611775 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) y: 0.9920150584836676 dimensionless dydx: [, ] logspace stuff at 12.0285 seconds Starting iteration 5 at 12.0848 seconds AR : 9.999999999611775 dimensionless CD : 0.07208383829260291 dimensionless CL : 0.9999998115160276 dimensionless S : 0.6639218067517705 meter ** 2 V : 3.600069044356998 meter / second W : 5.270412465184867 newton Wwing : 0.20138432032400524 newton e : 0.9921187131764531 dimensionless lam : 0.40055731597956656 dimensionless Calling cvxopt.solvers.cp at 12.0982 seconds Got sol from cvxopt at 12.1332 seconds status optimal x [ 8.00e-13] [ 4.58e-05] [ 4.24e-09] [-2.43e-10] [-1.58e-09] [ 8.36e-10] [-3.65e-10] [-1.03e-04] [-4.33e-03] [-2.09e-21] [ 2.29e-21] [ 2.23e-16] [ 5.49e-17] [ 2.19e-16] [ 1.20e-26] [ 5.00e-16] [ 6.74e-26] y [-4.18e-06] [ 4.57e-06] [ 4.45e-01] znl [ 1.00e+00] [ 1.35e-10] zl [ 1.10e-01] [ 4.39e-01] [ 2.41e-11] snl [ 1.96e-11] [ 2.03e-01] sl [ 1.84e-07] [ 3.80e-11] [ 8.74e-01] gap 2.0319558430018127e-08 relative gap 7.72642316948719e-09 primal objective -2.629879050666436 dual objective -2.6298790609642557 primal slack 1.9617027174043307e-11 dual slack 2.4096853737193532e-11 primal infeasibility 2.9323641616395997e-09 dual infeasibility 2.9672633006208335e-09 AVL run case - lam, AR: 0.39882645454821797 9.999999999619773 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) y: 0.9920158805953564 dimensionless dydx: [, ] logspace stuff at 13.8044 seconds Starting iteration 6 at 13.8913 seconds AR : 9.999999999619773 dimensionless CD : 0.07208714305299325 dimensionless CL : 0.9999998157581855 dimensionless S : 0.6639218065905538 meter ** 2 V : 3.6000690386621352 meter / second W : 5.270412469588729 newton Wwing : 0.20138432025057307 newton e : 0.9920165401543815 dimensionless lam : 0.39882645454821797 dimensionless Calling cvxopt.solvers.cp at 13.9046 seconds Got sol from cvxopt at 13.9412 seconds status optimal x [ 2.35e-13] [ 2.97e-07] [ 1.09e-09] [-5.55e-11] [-3.69e-10] [ 2.96e-10] [-8.34e-11] [-6.65e-07] [-3.26e-05] [ 1.22e-24] [-1.28e-24] [ 2.23e-16] [ 5.49e-17] [ 2.19e-16] [ 1.20e-26] [ 5.00e-16] [ 6.76e-26] y [ 2.45e-09] [-2.57e-09] [ 4.45e-01] znl [ 1.00e+00] [ 1.35e-10] zl [ 1.10e-01] [ 4.39e-01] [ 2.40e-11] snl [ 1.95e-11] [ 2.03e-01] sl [ 1.83e-07] [ 3.78e-11] [ 8.74e-01] gap 2.0211071384418575e-08 relative gap 7.685171307020508e-09 primal objective -2.6298790979396243 dual objective -2.6298791081822794 primal slack 1.9527381358931494e-11 dual slack 2.3958347059954e-11 primal infeasibility 2.91563113889845e-09 dual infeasibility 2.9337880900448994e-09 AVL run case - lam, AR: 0.3988134371869373 9.999999999622123 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing, index = 1 Getting vortex lattice surface data VLM surface name - wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - wing (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) y: 0.9920158812322937 dimensionless dydx: [, ] logspace stuff at 15.5530 seconds Objective --------- 0.072 dimensionless Variables --------- AR : 10.000 [-] Wing aspect ratio CD : 0.072 [-] Drag Coefficient CL : 1.000 [-] Lift Coefficient S : 0.664 meter ** 2 Wing area V : 3.600 meter / second Airspeed W : 5.270 newton Aircraft weight Wwing : 0.201 newton Wing weight e : 0.992 [-] Oswald efficiency factor lam : 0.399 [-] Wing taper ratio Sensitivities ------------- Sensitivities not available for optimizations of type Sequential Log Convex Program Solve Report ------------ Solve Method : Sequential Log Convex Program Classification : Iterative Solver : cvxopt Number of Iterations : 7 Termination Status : Converged, gradient of Lagrangian (1.043845e-07) within tolerance (1.000000e-06) Messages -------- 1. Wolfe Condition 1 failed at iteration 3 (Step 3). Watchdog counter is 1 13.872092548132564 real 0m18.301s user 0m11.217s sys 0m5.810s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case pyCAPS/optWingAvl.py passed (as expected) ================================================= ================================================= + echo 'pyCAPS/GPSize.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt pyCAPS/GPSize.py test; + python -u pyCAPS/GPSize.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Objective --------- 6339.9402476213 newton Variables --------- AR : 18.0583068591 [-] aspect ratio C_D_0 : 0.0127966186 [-] Drag Coefficient, segment 0 C_D_1 : 0.0128135534 [-] Drag Coefficient, segment 1 C_D_2 : 0.0077622395 [-] Drag Coefficient, segment 2 C_Dfuse_0 : 0.0017626506 [-] Fuselage Drag Coefficient, segment 0 C_Dfuse_1 : 0.0017626506 [-] Fuselage Drag Coefficient, segment 1 C_Dfuse_2 : 0.0017626510 [-] Fuselage Drag Coefficient, segment 2 C_Di_0 : 0.0056016002 [-] Induced Drag Coefficient, segment 0 C_Di_1 : 0.0056028716 [-] Induced Drag Coefficient, segment 1 C_Di_2 : 0.0002594009 [-] Induced Drag Coefficient, segment 2 C_Dp_0 : 0.0054327043 [-] Wing Profile Drag Coefficient, segment 0 C_Dp_1 : 0.0054483614 [-] Wing Profile Drag Coefficient, segment 1 C_Dp_2 : 0.0057382717 [-] Wing Profile Drag Coefficient, segment 2 C_L_0 : 0.5494535783 [-] Lift Coefficient, segment 0 C_L_1 : 0.5495159270 [-] Lift Coefficient, segment 1 C_L_2 : 0.1182390122 [-] Lift Coefficient, segment 2 I_cap_bar : 0.0000193397 [-] Area moment of inertia of cap on 2D cross section, normalized by chord^4 M_r_bar : 32106.9717613474 newton Root Bending unit per unit chord P_max : 1211155.7559680410 watt Maximum Engine Power R : 4999.9816129528 kilometer Single Segment range Re_0 : 4636790.3991634697 [-] Reynolds Number, segment 0 Re_1 : 4427330.4209076529 [-] Reynolds Number, segment 1 Re_2 : 9995446.9239517339 [-] Reynolds Number, segment 2 S : 28.3664420021 meter ** 2 total wing area T_0 : 799.0178645705 newton Thrust, segment 0 T_1 : 729.4239244544 newton Thrust, segment 1 T_2 : 2252.7493855701 newton Thrust, segment 2 V_0 : 69.5874592840 meter / second Velocity, segment 0 V_1 : 66.4439512429 meter / second Velocity, segment 1 V_2 : 150.0084591036 meter / second Velocity, segment 2 V_stall : 37.9986643205 meter / second stall speed W_0 : 34307.5807516552 newton Weight, segment 0 W_1 : 31281.5531631161 newton Weight, segment 1 W_2 : 34307.5610637156 newton Weight, segment 2 W_MTO : 37630.4011124297 newton Maximum Takeoff Weight W_cap : 4278.1047592241 newton Weight of Wing Spar Cap W_eng : 2854.2361754189 newton Engine Weight W_fuel_out : 3314.0247993997 newton Weight of fuel, outbound W_fuel_ret : 3025.9122892774 newton Weight of fuel, return W_pay : 4905.2326701420 newton Payload Weight W_tilde : 22457.8594632444 newton Dry Weight, no wing W_web : 133.6940460361 newton Weight of Wing Spar Shear Web W_wing : 8823.3040844200 newton wing weight W_zfw : 31281.2018350684 newton Zero Fuel Weight eta_0_0 : 0.2693167459 [-] Overall Efficiency, segment 0 eta_0_1 : 0.2692858916 [-] Overall Efficiency, segment 1 eta_0_2 : 0.2791280518 [-] Overall Efficiency, segment 2 eta_i_0 : 0.9052651192 [-] Inviscid Propeller Efficiency, segment 0 eta_i_1 : 0.9051614203 [-] Inviscid Propeller Efficiency, segment 1 eta_i_2 : 0.9382448822 [-] Inviscid Propeller Efficiency, segment 2 eta_prop_0 : 0.7694756986 [-] Propeller Efficiency, segment 0 eta_prop_1 : 0.7693875506 [-] Propeller Efficiency, segment 1 eta_prop_2 : 0.7975082496 [-] Propeller Efficiency, segment 2 nu : 0.7860410805 [-] Placeholder, (1+lam_w+lam_w**2)/(1+lam_w)**2 p : 1.9000448519 [-] Dummy Variable (1+2*lam_w) q : 1.4500404597 [-] Dummy Variable (1+lam_w) t_cap_bar : 0.0043345438 [-] Spar cap thickness per unit chord t_web_bar : 0.0006000270 [-] Spar web thickness per unit chord tau : 0.1499996279 [-] airfoil thickness to chord ratio z_bre_0 : 0.0922115805 [-] Breguet Range Factor, segment 0 z_bre_1 : 0.0923337617 [-] Breguet Range Factor, segment 1 Constants --------- A_prop : 0.7850000000 meter ** 2 Disk area of propeller CDA0 : 0.0500000000 meter ** 2 fuselage drag area C_Lmax : 1.5000000000 [-] max CL with flaps down N_lift : 6 [-] Ultimate Load Factor W_fixed : 14700 newton fixed weight e : 0.9500000000 [-] Oswald efficiency factor eta_eng : 0.3500000000 [-] Engine Efficiency eta_v : 0.8500000000 [-] Propeller Viscous Efficiency f_wadd : 2 [-] Added Weight Fraction g : 9.8100000000 meter / second ** 2 Gravitational constant h_fuel : 46000000 joule / kilogram Fuel Specific energy density k_ew : 0.0372000000 newton / watt ** 0.803 Constant for engine weight mu : 0.0000171000 kilogram / meter / second viscosity of air r_h : 0.7500000000 [-] Ratio of height at rear spar to maximum wing height rho : 0.9091220000 kilogram / meter ** 3 density of air rho_SL : 1.2250000000 kilogram / meter ** 3 density of air, sea level rho_cap : 2700 kilogram / meter ** 3 Density of wing cap material (aluminum) rho_web : 2700 kilogram / meter ** 3 Density of wing web material (aluminum) sigma_max : 250 megapascal Allowable tensile stress of aluminum sigma_max_shear : 167 megapascal Allowable shear stress of aluminum w_bar : 0.5000000000 [-] Ratio of spar box width to chord length Sensitivities ------------- Sensitivities not computed Solve Report ------------ Solve Method : Geometric Program Classification : Convex Solver : cvxopt EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! real 0m15.958s user 0m15.166s sys 0m0.991s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case pyCAPS/GPSize.py passed (as expected) ================================================= mses: /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/mses ================================================= + echo 'pyCAPS/MSES.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt pyCAPS/MSES.py test; + python -u pyCAPS/MSES.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Objective --------- 6436.3912141344 newton Variables --------- AR : 17.9064478129 [-] aspect ratio Alpha_p20_MSES_0 : 22.7211519990 degree Angle of Attack + 20deg from MSES, segment 0 Alpha_p20_MSES_1 : 22.6953218092 degree Angle of Attack + 20deg from MSES, segment 1 Alpha_p20_MSES_2 : 18.8665108253 degree Angle of Attack + 20deg from MSES, segment 2 C_D_0 : 0.0128868885 [-] Drag Coefficient, segment 0 C_D_1 : 0.0128291749 [-] Drag Coefficient, segment 1 C_D_2 : 0.0074753921 [-] Drag Coefficient, segment 2 C_Dfuse_0 : 0.0017722656 [-] Fuselage Drag Coefficient, segment 0 C_Dfuse_1 : 0.0017722656 [-] Fuselage Drag Coefficient, segment 1 C_Dfuse_2 : 0.0017722656 [-] Fuselage Drag Coefficient, segment 2 C_Di_0 : 0.0054778078 [-] Induced Drag Coefficient, segment 0 C_Di_1 : 0.0054168632 [-] Induced Drag Coefficient, segment 1 C_Di_2 : 0.0002607206 [-] Induced Drag Coefficient, segment 2 C_Dp_0 : 0.0056368154 [-] Wing Profile Drag Coefficient, segment 0 C_Dp_1 : 0.0056400462 [-] Wing Profile Drag Coefficient, segment 1 C_Dp_2 : 0.0054424037 [-] Wing Profile Drag Coefficient, segment 2 C_L_0 : 0.5410592839 [-] Lift Coefficient, segment 0 C_L_1 : 0.5380410261 [-] Lift Coefficient, segment 1 C_L_2 : 0.1180399880 [-] Lift Coefficient, segment 2 C_L_MSES_0 : 0.5410592839 [-] Lift Coefficient from MSES, segment 0 C_L_MSES_1 : 0.5380410261 [-] Lift Coefficient from MSES, segment 1 C_L_MSES_2 : 0.1180399880 [-] Lift Coefficient from MSES, segment 2 I_cap_bar : 0.0000190294 [-] Area moment of inertia of cap on 2D cross section, normalized by chord^4 M_r_bar : 31688.9338344574 newton Root Bending unit per unit chord P_max : 1156269.6009418026 watt Maximum Engine Power R : 5000.0000009406 kilometer Single Segment range Re_0 : 4675471.1359547451 [-] Reynolds Number, segment 0 Re_1 : 4472446.0471084677 [-] Reynolds Number, segment 1 Re_2 : 10009980.4347200561 [-] Reynolds Number, segment 2 S : 28.2124755016 meter ** 2 total wing area T_0 : 811.2380859869 newton Thrust, segment 0 T_1 : 738.9898037834 newton Thrust, segment 1 T_2 : 2156.9995885670 newton Thrust, segment 2 V_0 : 70.0621477319 meter / second Velocity, segment 0 V_1 : 67.0198075368 meter / second Velocity, segment 1 V_2 : 150.0000123234 meter / second Velocity, segment 2 V_stall : 37.9999995456 meter / second stall speed W_0 : 34060.0367985338 newton Weight, segment 0 W_1 : 30992.3930809630 newton Weight, segment 1 W_2 : 34060.0367985338 newton Weight, segment 2 W_MTO : 37428.7850409815 newton Maximum Takeoff Weight W_cap : 4187.4657136299 newton Weight of Wing Spar Cap W_eng : 2749.0298144962 newton Engine Weight W_fuel_out : 3368.7476046609 newton Weight of fuel, outbound W_fuel_ret : 3067.6436094735 newton Weight of fuel, return W_pay : 4905.0000770013 newton Payload Weight W_tilde : 22354.0298493220 newton Dry Weight, no wing W_web : 131.7165615697 newton Weight of Wing Spar Shear Web W_wing : 8638.3641164558 newton wing weight W_zfw : 30992.3930605310 newton Zero Fuel Weight eta_0_0 : 0.2692787194 [-] Overall Efficiency, segment 0 eta_0_1 : 0.2693832845 [-] Overall Efficiency, segment 1 eta_0_2 : 0.2798223310 [-] Overall Efficiency, segment 2 eta_i_0 : 0.9051385526 [-] Inviscid Propeller Efficiency, segment 0 eta_i_1 : 0.9054900321 [-] Inviscid Propeller Efficiency, segment 1 eta_i_2 : 0.9405792639 [-] Inviscid Propeller Efficiency, segment 2 eta_prop_0 : 0.7693677697 [-] Propeller Efficiency, segment 0 eta_prop_1 : 0.7696665273 [-] Propeller Efficiency, segment 1 eta_prop_2 : 0.7994923743 [-] Propeller Efficiency, segment 2 nu : 0.7859964130 [-] Placeholder, (1+lam_w+lam_w**2)/(1+lam_w)**2 p : 1.9000000028 [-] Dummy Variable (1+2*lam_w) q : 1.4500000050 [-] Dummy Variable (1+lam_w) t_cap_bar : 0.0042599266 [-] Spar cap thickness per unit chord t_web_bar : 0.0005954185 [-] Spar web thickness per unit chord tau : 0.1499999997 [-] airfoil thickness to chord ratio z_bre_0 : 0.0943153467 [-] Breguet Range Factor, segment 0 z_bre_1 : 0.0943830203 [-] Breguet Range Factor, segment 1 Sensitivities ------------- Sensitivities not available for optimizations of type Sequential Log Convex Program Solve Report ------------ Solve Method : Sequential Log Convex Program Classification : Iterative Solver : cvxopt Number of Iterations : 16 Termination Status : Converged, relative change in the objective function (8.64e-06) is witin specified tolerance (1.00e-05) Messages -------- 1. Attempted step of size 1.00e+00 at iteration 2 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 2. Attempted step of size 9.00e-01 at iteration 2 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 3. Wolfe Condition 1 failed at iteration 4 (Step 4). Watchdog counter is 1 4. Wolfe Condition 1 failed at iteration 7 (Step 7). Watchdog counter is 1 5. Wolfe Condition 1 failed at iteration 10 (Step 10). Watchdog counter is 1 6. Wolfe Condition 1 failed at iteration 11 (Step 11). Watchdog counter is 2 7. Wolfe Condition 1 failed at iteration 12 (Step 12). Watchdog counter is 3 real 4m0.279s user 3m45.862s sys 0m11.188s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case pyCAPS/MSES.py passed (as expected) ================================================= ================================================= + echo 'pyCAPS/Camber.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt pyCAPS/Camber.py test; + python -u pyCAPS/Camber.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 maxloc = 1.002482 >= 1 ERROR:: (egads_rangerr) in Branch Brch_000043 at [[/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/corsairlite/multifidelity/hoburg/Camber/capsCSMFiles/naca.csm:62]] maxloc = 1.002482 >= 1 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Objective --------- 5444.9476280478 newton Variables --------- AR : 18.4901973512 [-] aspect ratio Alpha_p20_MSES_0 : 17.9528371532 degree Angle of Attack + 20deg from MSES, segment 0 Alpha_p20_MSES_1 : 18.0474152851 degree Angle of Attack + 20deg from MSES, segment 1 Alpha_p20_MSES_2 : 14.3726836491 degree Angle of Attack + 20deg from MSES, segment 2 C_D_0 : 0.0109818327 [-] Drag Coefficient, segment 0 C_D_1 : 0.0112190590 [-] Drag Coefficient, segment 1 C_D_2 : 0.0067072042 [-] Drag Coefficient, segment 2 C_Dfuse_0 : 0.0018227711 [-] Fuselage Drag Coefficient, segment 0 C_Dfuse_1 : 0.0018227711 [-] Fuselage Drag Coefficient, segment 1 C_Dfuse_2 : 0.0018227711 [-] Fuselage Drag Coefficient, segment 2 C_Di_0 : 0.0050991382 [-] Induced Drag Coefficient, segment 0 C_Di_1 : 0.0053109555 [-] Induced Drag Coefficient, segment 1 C_Di_2 : 0.0002596858 [-] Induced Drag Coefficient, segment 2 C_Dp_0 : 0.0040599234 [-] Wing Profile Drag Coefficient, segment 0 C_Dp_1 : 0.0040853325 [-] Wing Profile Drag Coefficient, segment 1 C_Dp_2 : 0.0046247461 [-] Wing Profile Drag Coefficient, segment 2 C_L_0 : 0.5301555732 [-] Lift Coefficient, segment 0 C_L_1 : 0.5408804300 [-] Lift Coefficient, segment 1 C_L_2 : 0.1196310531 [-] Lift Coefficient, segment 2 C_L_MSES_0 : 0.5301555732 [-] Lift Coefficient from MSES, segment 0 C_L_MSES_1 : 0.5408804300 [-] Lift Coefficient from MSES, segment 1 C_L_MSES_2 : 0.1196310531 [-] Lift Coefficient from MSES, segment 2 I_cap_bar : 0.0000205274 [-] Area moment of inertia of cap on 2D cross section, normalized by chord^4 M_r_bar : 32282.9387918620 newton Root Bending unit per unit chord P_max : 1001419.9954321110 watt Maximum Engine Power R : 5000.0000016548 kilometer Single Segment range Re_0 : 4626593.0529566435 [-] Reynolds Number, segment 0 Re_1 : 4400555.1302864701 [-] Reynolds Number, segment 1 Re_2 : 9717957.1433745287 [-] Reynolds Number, segment 2 S : 27.4391704426 meter ** 2 total wing area T_0 : 696.2621974610 newton Thrust, segment 0 T_1 : 642.8205037338 newton Thrust, segment 1 T_2 : 1881.6565831794 newton Thrust, segment 2 V_0 : 71.3878188257 meter / second Velocity, segment 0 V_1 : 67.8976808420 meter / second Velocity, segment 1 V_2 : 150.0000079267 meter / second Velocity, segment 2 V_stall : 37.9999897863 meter / second stall speed W_0 : 33573.5550654004 newton Weight, segment 0 W_1 : 30957.3717720614 newton Weight, segment 1 W_2 : 33573.5550654004 newton Weight, segment 2 W_MTO : 36402.8422115107 newton Maximum Takeoff Weight W_cap : 4321.3600258130 newton Weight of Wing Spar Cap W_eng : 2449.1885460739 newton Engine Weight W_fuel_out : 2828.7644163103 newton Weight of fuel, outbound W_fuel_ret : 2616.1832117374 newton Weight of fuel, return W_pay : 4905.0000311107 newton Payload Weight W_tilde : 22054.1885403676 newton Dry Weight, no wing W_web : 130.2317539101 newton Weight of Wing Spar Shear Web W_wing : 8903.1832157470 newton wing weight W_zfw : 30957.3717490756 newton Zero Fuel Weight camberLocation : 0.7425836997 [-] location of maximum airfoil camber scaled by chord eta_0_0 : 0.2733861489 [-] Overall Efficiency, segment 0 eta_0_1 : 0.2729458786 [-] Overall Efficiency, segment 1 eta_0_2 : 0.2818547308 [-] Overall Efficiency, segment 2 eta_i_0 : 0.9189450383 [-] Inviscid Propeller Efficiency, segment 0 eta_i_1 : 0.9174651383 [-] Inviscid Propeller Efficiency, segment 1 eta_i_2 : 0.9474108599 [-] Inviscid Propeller Efficiency, segment 2 eta_prop_0 : 0.7811032825 [-] Propeller Efficiency, segment 0 eta_prop_1 : 0.7798453676 [-] Propeller Efficiency, segment 1 eta_prop_2 : 0.8052992309 [-] Propeller Efficiency, segment 2 maxCamber : 0.0424943188 [-] maximum airfoil camber scaled by chord nu : 0.7859963990 [-] Placeholder, (1+lam_w+lam_w**2)/(1+lam_w)**2 p : 1.9000000016 [-] Dummy Variable (1+2*lam_w) q : 1.4500000030 [-] Dummy Variable (1+lam_w) t_cap_bar : 0.0046546586 [-] Spar cap thickness per unit chord t_web_bar : 0.0006253929 [-] Spar web thickness per unit chord tau : 0.1495437269 [-] airfoil thickness to chord ratio z_bre_0 : 0.0809143871 [-] Breguet Range Factor, segment 0 z_bre_1 : 0.0811481449 [-] Breguet Range Factor, segment 1 Sensitivities ------------- Sensitivities not available for optimizations of type Sequential Log Convex Program Solve Report ------------ Solve Method : Sequential Log Convex Program Classification : Iterative Solver : cvxopt Number of Iterations : 44 Termination Status : Converged, relative change in the objective function (3.04e-07) is witin specified tolerance (1.00e-05) Messages -------- 1. Attempted step of size 1.00e+00 at iteration 4 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 2. Wolfe Condition 1 failed at iteration 5 (Step 5). Watchdog counter is 1 3. Wolfe Condition 1 failed at iteration 7 (Step 7). Watchdog counter is 1 4. Wolfe Condition 1 failed at iteration 8 (Step 8). Watchdog counter is 2 5. Attempted step of size 1.00e+00 at iteration 9 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 6. Attempted step of size 1.00e+00 at iteration 10 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 7. Wolfe Condition 1 failed at iteration 11 (Step 11). Watchdog counter is 1 8. Wolfe Condition 1 failed at iteration 13 (Step 13). Watchdog counter is 1 9. Wolfe Condition 1 failed at iteration 16 (Step 16). Watchdog counter is 1 10. Wolfe Condition 1 failed at iteration 18 (Step 18). Watchdog counter is 1 11. Attempted step of size 2.37e-01 at iteration 25 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 12. Attempted step of size 7.12e-02 at iteration 25 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 13. Wolfe Condition 1 failed at iteration 25 (Step 25). Watchdog counter is 1 14. Wolfe Condition 1 failed at iteration 32 (Step 32). Watchdog counter is 1 15. Wolfe Condition 1 failed at iteration 34 (Step 34). Watchdog counter is 1 16. Wolfe Condition 1 failed at iteration 35 (Step 35). Watchdog counter is 2 17. Wolfe Condition 1 failed at iteration 36 (Step 36). Watchdog counter is 3 18. Wolfe Condition 1 failed at iteration 42 (Step 42). Watchdog counter is 1 real 11m19.505s user 10m18.427s sys 0m32.366s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case pyCAPS/Camber.py passed (as expected) ================================================= ================================================= + echo 'pyCAPS/CMConstraint.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt pyCAPS/CMConstraint.py test; + python -u pyCAPS/CMConstraint.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/CAPSexamples/regressionTest/pyCAPSlog.txt Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Getting CFD design variables....... Number of design variables - 3 Design Variable name - camber Design Variable name - maxloc Design Variable name - thickness Done getting CFD design variables CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 CAPS Info: Sensitivity FD step 1.000000e-05 Objective --------- 6394.7504675664 newton Variables --------- AR : 17.8913753447 [-] aspect ratio Alpha_p20_MSES_0 : 22.3270790919 degree Angle of Attack + 20deg from MSES, segment 0 Alpha_p20_MSES_1 : 22.3914756112 degree Angle of Attack + 20deg from MSES, segment 1 Alpha_p20_MSES_2 : 18.5106875432 degree Angle of Attack + 20deg from MSES, segment 2 C_D_0 : 0.0127821144 [-] Drag Coefficient, segment 0 C_D_1 : 0.0129251719 [-] Drag Coefficient, segment 1 C_D_2 : 0.0075836100 [-] Drag Coefficient, segment 2 C_Dfuse_0 : 0.0017725945 [-] Fuselage Drag Coefficient, segment 0 C_Dfuse_1 : 0.0017725945 [-] Fuselage Drag Coefficient, segment 1 C_Dfuse_2 : 0.0017725945 [-] Fuselage Drag Coefficient, segment 2 C_Di_0 : 0.0054658617 [-] Induced Drag Coefficient, segment 0 C_Di_1 : 0.0055913053 [-] Induced Drag Coefficient, segment 1 C_Di_2 : 0.0002612825 [-] Induced Drag Coefficient, segment 2 C_Dp_0 : 0.0055436584 [-] Wing Profile Drag Coefficient, segment 0 C_Dp_1 : 0.0055612722 [-] Wing Profile Drag Coefficient, segment 1 C_Dp_2 : 0.0055497273 [-] Wing Profile Drag Coefficient, segment 2 C_L_0 : 0.5400363899 [-] Lift Coefficient, segment 0 C_L_1 : 0.5462287478 [-] Lift Coefficient, segment 1 C_L_2 : 0.1181168079 [-] Lift Coefficient, segment 2 C_L_MSES_0 : 0.5400363899 [-] Lift Coefficient from MSES, segment 0 C_L_MSES_1 : 0.5462287478 [-] Lift Coefficient from MSES, segment 1 C_L_MSES_2 : 0.1181168079 [-] Lift Coefficient from MSES, segment 2 I_cap_bar : 0.0000190292 [-] Area moment of inertia of cap on 2D cross section, normalized by chord^4 M_r_bar : 31709.4081507628 newton Root Bending unit per unit chord P_max : 1173731.2996940832 watt Maximum Engine Power R : 5000.0000185573 kilometer Single Segment range Re_0 : 4684429.6694883015 [-] Reynolds Number, segment 0 Re_1 : 4444409.0185610838 [-] Reynolds Number, segment 1 Re_2 : 10013302.6010992285 [-] Reynolds Number, segment 2 S : 28.2072955874 meter ** 2 total wing area T_0 : 806.6032366274 newton Thrust, segment 0 T_1 : 734.2363339161 newton Thrust, segment 1 T_2 : 2187.8204431749 newton Thrust, segment 2 V_0 : 70.1727920571 meter / second Velocity, segment 0 V_1 : 66.5771317503 meter / second Velocity, segment 1 V_2 : 150.0000250137 meter / second Velocity, segment 2 V_stall : 37.9999989707 meter / second stall speed W_0 : 34075.9562944454 newton Weight, segment 0 W_1 : 31027.1592613867 newton Weight, segment 1 W_2 : 34075.9562944454 newton Weight, segment 2 W_MTO : 37421.9118468609 newton Maximum Takeoff Weight W_cap : 4188.0636047371 newton Weight of Wing Spar Cap W_eng : 2782.3174517949 newton Engine Weight W_fuel_out : 3345.9535538813 newton Weight of fuel, outbound W_fuel_ret : 3048.7969136851 newton Weight of fuel, return W_pay : 4905.0003715348 newton Payload Weight W_tilde : 22387.3178053338 newton Dry Weight, no wing W_web : 131.8568932923 newton Weight of Wing Spar Shear Web W_wing : 8639.8409715248 newton wing weight W_zfw : 31027.1589167478 newton Zero Fuel Weight camberLocation : 0.3845642839 [-] location of maximum airfoil camber scaled by chord eta_0_0 : 0.2694753058 [-] Overall Efficiency, segment 0 eta_0_1 : 0.2692157528 [-] Overall Efficiency, segment 1 eta_0_2 : 0.2795983708 [-] Overall Efficiency, segment 2 eta_i_0 : 0.9057993471 [-] Inviscid Propeller Efficiency, segment 0 eta_i_1 : 0.9049269001 [-] Inviscid Propeller Efficiency, segment 1 eta_i_2 : 0.9398264564 [-] Inviscid Propeller Efficiency, segment 2 eta_prop_0 : 0.7699294450 [-] Propeller Efficiency, segment 0 eta_prop_1 : 0.7691878651 [-] Propeller Efficiency, segment 1 eta_prop_2 : 0.7988524879 [-] Propeller Efficiency, segment 2 maxCamber : 0.0236403205 [-] maximum airfoil camber scaled by chord negCMp1_0 : 1.0578681152 [-] Negative CM about 0.25c + 1, segment 0 negCMp1_1 : 1.0576218708 [-] Negative CM about 0.25c + 1, segment 1 negCMp1_2 : 1.0596323386 [-] Negative CM about 0.25c + 1, segment 2 nu : 0.7859964982 [-] Placeholder, (1+lam_w+lam_w**2)/(1+lam_w)**2 p : 1.9000000145 [-] Dummy Variable (1+2*lam_w) q : 1.4500000244 [-] Dummy Variable (1+lam_w) t_cap_bar : 0.0042598978 [-] Spar cap thickness per unit chord t_web_bar : 0.0005959117 [-] Spar web thickness per unit chord tau : 0.1499998633 [-] airfoil thickness to chord ratio z_bre_0 : 0.0936645407 [-] Breguet Range Factor, segment 0 z_bre_1 : 0.0937293082 [-] Breguet Range Factor, segment 1 Sensitivities ------------- Sensitivities not available for optimizations of type Sequential Log Convex Program Solve Report ------------ Solve Method : Sequential Log Convex Program Classification : Iterative Solver : cvxopt Number of Iterations : 23 Termination Status : Converged, relative change in the objective function (1.10e-06) is witin specified tolerance (1.00e-05) Messages -------- 1. Wolfe Condition 1 failed at iteration 2 (Step 2). Watchdog counter is 1 2. Wolfe Condition 1 failed at iteration 3 (Step 3). Watchdog counter is 2 3. Wolfe Condition 1 failed at iteration 4 (Step 4). Watchdog counter is 3 4. Attempted step of size 1.00e+00 at iteration 5 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 5. Wolfe Condition 1 failed at iteration 8 (Step 8). Watchdog counter is 1 6. Wolfe Condition 1 failed at iteration 9 (Step 9). Watchdog counter is 2 7. Attempted step of size 1.00e+00 at iteration 10 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 8. Attempted step of size 3.00e-01 at iteration 10 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 9. Attempted step of size 1.00e+00 at iteration 11 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 10. Attempted step of size 1.00e+00 at iteration 12 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 11. Wolfe Condition 1 failed at iteration 14 (Step 14). Watchdog counter is 1 12. Wolfe Condition 1 failed at iteration 15 (Step 15). Watchdog counter is 2 13. Wolfe Condition 1 failed at iteration 16 (Step 16). Watchdog counter is 3 14. Wolfe Condition 1 failed at iteration 18 (Step 18). Watchdog counter is 1 15. Attempted step of size 3.81e-01 at iteration 19 is too large and is causing a constraint to return as imaginary. Decreasing according to the tau schedule. 16. Wolfe Condition 1 failed at iteration 21 (Step 21). Watchdog counter is 1 17. Wolfe Condition 1 failed at iteration 22 (Step 22). Watchdog counter is 2 real 7m11.350s user 6m35.120s sys 0m19.326s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case pyCAPS/CMConstraint.py passed (as expected) ================================================= Traceback (most recent call last): File "", line 1, in ModuleNotFoundError: No module named 'torch' ************************************************* ************************************************* ================================================= Did not run examples for: awave autoLink Pointwise Cart3D Fun3D abaqus Nastran Mystran Plato Mystran ================================================= All tests pass! ================================================= ================================================= + cd /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023 + bash -e execute_Training.sh ================================================= Using python : /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/bin/python ================================================= ================================================= + echo 'transport.csm test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log transport.csm test; + /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveESP -batch -verify -outLevel 0 transport.csm + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.8.1/transport.vfy", so verification is being skipped MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle MESSAGE:: Building wingHinges MESSAGE:: Building nacelleOml MESSAGE:: Building htailOml MESSAGE:: Building htailWaffle MESSAGE:: Building htailHinges MESSAGE:: Building vtailOml MESSAGE:: Building vtailWaffle MESSAGE:: Building vtailHinges MESSAGE:: Building fuseOml MESSAGE:: Building fuseWaffle MESSAGE:: Building fuseIml MESSAGE:: Building payload ==> serveESP completed successfully with 5 warnings and no verification data real 0m21.109s user 0m26.298s sys 0m3.263s + status=0 + set +x ================================================= data/ESP/transport passed (as expected) ================================================= execute_Training.sh: line 157: /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/test/template_avl: No such file or directory ================================================= template_avl.py test; + python template_avl.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Creating AVL aim... {'wingHinge1': {'deflectionAngle': -10.0}, 'wingHinge2': {'deflectionAngle': 10.0}, 'wingHinge3': {'deflectionAngle': 15.0}, 'wingHinge4': {'deflectionAngle': 15.0}, 'wingHinge5': {'deflectionAngle': 10.0}, 'wingHinge6': {'deflectionAngle': 10.0}, 'htailHinge1': {'deflectionAngle': 5.0}, 'htailHinge2': {'deflectionAngle': 5.0}} ==> Running AVL... MESSAGE:: Building wingOml MESSAGE:: Building wingHinges MESSAGE:: Building htailOml MESSAGE:: Building htailHinges MESSAGE:: Building vtailOml MESSAGE:: Building vtailHinges Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice control surface data VLM control surface name - htailHinge1 VLM control surface name - htailHinge2 VLM control surface name - wingHinge1 VLM control surface name - wingHinge2 VLM control surface name - wingHinge3 VLM control surface name - wingHinge4 VLM control surface name - wingHinge5 VLM control surface name - wingHinge6 Done getting vortex lattice control surface data Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control WingControl1 not found in controls tuple! Only defaults will be used. Warning: Control WingControl1 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl4 not found in controls tuple! Only defaults will be used. Warning: Control WingControl4 not found in controls tuple! Only defaults will be used. Writing surface - Htail (ID = 0) Section 1 of 7 (ID = 0) Section 2 of 7 (ID = 3) Control surface 1 of 1 Section 3 of 7 (ID = 4) Control surface 1 of 1 Section 4 of 7 (ID = 1) Section 5 of 7 (ID = 5) Control surface 1 of 1 Section 6 of 7 (ID = 6) Control surface 1 of 1 Section 7 of 7 (ID = 2) Writing surface - Wing (ID = 1) Section 1 of 17 (ID = 0) Section 2 of 17 (ID = 5) Control surface 1 of 1 Section 3 of 17 (ID = 6) Control surface 1 of 1 Section 4 of 17 (ID = 7) Control surface 1 of 1 Section 5 of 17 (ID = 8) Control surface 1 of 1 Section 6 of 17 (ID = 4) Section 7 of 17 (ID = 9) Control surface 1 of 1 Section 8 of 17 (ID = 10) Control surface 1 of 1 Section 9 of 17 (ID = 1) Section 10 of 17 (ID = 11) Control surface 1 of 1 Section 11 of 17 (ID = 12) Control surface 1 of 1 Section 12 of 17 (ID = 3) Section 13 of 17 (ID = 13) Control surface 1 of 1 Section 14 of 17 (ID = 14) Control surface 1 of 1 Section 15 of 17 (ID = 15) Control surface 1 of 1 Section 16 of 17 (ID = 16) Control surface 1 of 1 Section 17 of 17 (ID = 2) ================ run_avl.py complete ================== Force/moment coefficients: CXtot : 0.1440096424064962 CYtot : -2.354427059781186e-09 CZtot : -1.170781415636729 Cltot : -7.74027428929831e-12 Cmtot : -1.825894044461429 Cntot : -1.081704204546593e-10 CLtot : 1.178001627172014 CDtot : 0.06148224692119385 e : 0.7858933406059764 real 0m31.632s user 0m28.949s sys 0m9.346s + status=0 + set +x ================================================= data/session01/template_avl.py passed (as expected) ================================================= ================================================= + echo 'f118-A.csm test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log f118-A.csm test; + /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveESP -batch -verify -outLevel 0 f118-A.csm + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.8.1/f118-A.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.111s user 0m0.081s sys 0m0.028s + status=0 + set +x ================================================= data/session02/f118-A passed (as expected) ================================================= ================================================= 1_f118_Geom.py test; + python 1_f118_Geom.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-A.csm"... ==> Bulding and viewing geometry... real 0m1.323s user 0m0.848s sys 0m0.299s + status=0 + set +x ================================================= data/session02/1_f118_Geom.py passed (as expected) ================================================= ================================================= 2_f118_DESPMTR.py test; + python 2_f118_DESPMTR.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-A.csm"... --> old htail:area = 1210.0 --> new htail:area = 2420.0 ==> Bulding and viewing Wide Body geometry... ==> Bulding and viewing Canard geometry... ==> All design parameters --> wing:area = 1210.0 --> wing:aspect = 9.0 --> wing:thick = 0.1 --> wing:xroot = 54.0 --> wing:zroot = -5.0 --> htail:area = 4240.0 --> htail:aspect = 4.15 --> htail:thick = 0.08 --> htail:xroot = 145.0 --> htail:zroot = 5.0 --> vtail = [[1220.0, 1.8, 0.08, 150.0, -8.0, 9.0], [1220.0, 1.8, 0.08, 150.0, 8.0, 9.0]] --> fuse:length = 180.0 --> fuse:width = 20.0 --> fuse:height = 20.0 real 0m1.151s user 0m0.914s sys 0m0.328s + status=0 + set +x ================================================= data/session02/2_f118_DESPMTR.py passed (as expected) ================================================= ================================================= 3_f118_Save.py test; + python 3_f118_Save.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-A.csm"... --> old htail:area = 1210.0 --> new htail:area = 2420.0 ==> Bulding and saving Wide Body geometry... ==> Bulding and saving Canard geometry... ==> All design parameters --> wing:area = 1210.0 --> wing:aspect = 9.0 --> wing:thick = 0.1 --> wing:xroot = 54.0 --> wing:zroot = -5.0 --> htail:area = 4240.0 --> htail:aspect = 4.15 --> htail:thick = 0.08 --> htail:xroot = 145.0 --> htail:zroot = 5.0 --> vtail = [[1220.0, 1.8, 0.08, 150.0, -8.0, 9.0], [1220.0, 1.8, 0.08, 150.0, 8.0, 9.0]] --> fuse:length = 180.0 --> fuse:width = 20.0 --> fuse:height = 20.0 real 0m1.038s user 0m0.878s sys 0m0.288s + status=0 + set +x ================================================= data/session02/3_f118_Save.py passed (as expected) ================================================= ================================================= 4_f118_Shortcut.py test; + python 4_f118_Shortcut.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-A.csm"... --> old htail:area = 1210.0 --> new htail:area = 2420.0 ==> Bulding and viewing Wide Body geometry... ==> Bulding and viewing Canard geometry... ==> Grouped parameters --> fuse fuse:length = 180.0 fuse:width = 20.0 fuse:height = 20.0 --> wing wing:area = 1210.0 wing:aspect = 9.0 wing:thick = 0.1 wing:xroot = 54.0 wing:zroot = -5.0 --> htail htail:area = 4240.0 htail:aspect = 4.15 htail:thick = 0.08 htail:xroot = 145.0 htail:zroot = 5.0 real 0m1.185s user 0m0.938s sys 0m0.330s + status=0 + set +x ================================================= data/session02/4_f118_Shortcut.py passed (as expected) ================================================= ================================================= 5_f118_writeParameters.py test; + python 5_f118_writeParameters.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-A.csm"... ==> Saving parameters to "f118_4.params"... ==> Loading 2nd geometry from file "f118-A.csm"... ==> Reading parameters from "f118_4.params"... --> Opening DESPMTR file "f118_4.params" updating CFGPMTR nrow [ 1, 1] = 1.000000 updating DESPMTR wing:area [ 1, 1] = 4240.000000 updating DESPMTR wing:aspect [ 1, 1] = 9.000000 updating DESPMTR wing:thick [ 1, 1] = 0.100000 updating DESPMTR wing:xroot [ 1, 1] = 54.000000 updating DESPMTR wing:zroot [ 1, 1] = -5.000000 updating DESPMTR htail:area [ 1, 1] = 2420.000000 updating DESPMTR htail:aspect [ 1, 1] = 4.150000 updating DESPMTR htail:thick [ 1, 1] = 0.080000 updating DESPMTR htail:xroot [ 1, 1] = 145.000000 updating DESPMTR htail:zroot [ 1, 1] = 5.000000 updating DESPMTR vtail [ 1, 1] = 1220.000000 updating DESPMTR vtail [ 1, 2] = 1.800000 updating DESPMTR vtail [ 1, 3] = 0.080000 updating DESPMTR vtail [ 1, 4] = 150.000000 updating DESPMTR vtail [ 1, 5] = 0.000000 updating DESPMTR vtail [ 1, 6] = 9.000000 updating DESPMTR fuse:length [ 1, 1] = 180.000000 updating DESPMTR fuse:width [ 1, 1] = 60.000000 updating DESPMTR fuse:height [ 1, 1] = 20.000000 ==> Building and viewing the geometry... EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! real 0m1.229s user 0m0.903s sys 0m0.403s + status=0 + set +x ================================================= data/session02/5_f118_writeParameters.py passed (as expected) ================================================= ================================================= 6_f118_bodies.py test; + python 6_f118_bodies.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-A.csm"... ==> pyEGADS egos... Wing Htail Vtail1 Fuselage real 0m1.060s user 0m0.866s sys 0m0.287s + status=0 + set +x ================================================= data/session02/6_f118_bodies.py passed (as expected) ================================================= ================================================= + echo '7_f118_OUTPMTR.py test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log 7_f118_OUTPMTR.py test; + python 7_f118_OUTPMTR.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-A.csm"... --> wing:wet = 9422.222222222223 --> wing:volume = 9202.959910328365 --> htail:prop[0] = 2660.2506024096383 --> htail:prop[1] = 1652.8901595442062 --> vtail:prop = [1371.822222222222, None] --> fuse:wet = None --> fuse:volume = None Traceback (most recent call last): File "/Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/data/session02/7_f118_OUTPMTR.py", line 34, in print ("--> wing:span =", f118.outpmtr.wing.span ) ^^^^^^^^^^^^^^^^^^^^^^ File "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/pyESP/pyCAPS/problem.py", line 1954, in __getattr__ raise AttributeError("No Out Value: {!r}".format(name)) AttributeError: No Out Value: 'span' real 0m1.172s user 0m0.859s sys 0m0.274s + status=1 + set +x ================================================= data/session02/7_f118_OUTPMTR.py failed (as expected) ================================================= ================================================= 8_f118_Phasing.py test; + python 8_f118_Phasing.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-A.csm"... --> old htail:area = 1210.0 --> new htail:area = 2420.0 ==> Bulding and viewing Wide Body geometry... ==> Bulding and viewing geometry from WideBody phase... ==> Bulding and viewing Canard geometry... real 0m1.370s user 0m0.904s sys 0m0.483s + status=0 + set +x ================================================= data/session02/8_f118_Phasing.py passed (as expected) ================================================= ================================================= f118_Custom.py test; + python f118_Custom.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/session02/f118-A.csm"... ==> Bulding and viewing geometry... real 0m1.080s user 0m0.887s sys 0m0.298s + status=0 + set +x ================================================= solutions/session02/f118_Custom.py passed (as expected) ================================================= ================================================= + echo 'f118-B.csm test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log f118-B.csm test; + /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveESP -batch -verify -outLevel 0 f118-B.csm + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.8.1/f118-B.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.130s user 0m0.079s sys 0m0.022s + status=0 + set +x ================================================= data/session03/f118-B passed (as expected) ================================================= ================================================= + echo 'f118-C.csm test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log f118-C.csm test; + /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveESP -batch -verify -outLevel 0 f118-C.csm + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.8.1/f118-C.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.078s user 0m0.077s sys 0m0.021s + status=0 + set +x ================================================= data/session03/f118-C passed (as expected) ================================================= ================================================= + echo 'naca.csm test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log naca.csm test; + /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveESP -batch -verify -outLevel 0 naca.csm + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.8.1/naca.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.092s user 0m0.073s sys 0m0.021s + status=0 + set +x ================================================= data/session03/naca passed (as expected) ================================================= ================================================= 01_xfoil_input.py test; + python 01_xfoil_input.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... ==> Creating xfoilAIM ==> Modified Mach = 0.5 ==> Default Alpha = None ==> Modified Alpha = 2.5 ==> Modified Alpha = [0.0, 3.0, 5.0, 7.0, 8.0] ==> Unset Alpha = None EGADS Info: 0 Objects, 0 Reference in Use (of 0) at Close! real 0m1.058s user 0m0.895s sys 0m0.260s + status=0 + set +x ================================================= data/session03/01_xfoil_input.py passed (as expected) ================================================= ================================================= 02_xfoil_Analysis.py test; + python 02_xfoil_Analysis.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... ==> Creating xfoilAIM ==> Setting analysis values ==> Running preAnalysis ==> Running xFoil...... ==> Running postAnalysis ==> Retrieve analysis results --> Alpha = [0.0, 3.0, 5.0, 7.0, 8.0] --> Cl = [-3.53757485379788e-07, 0.377437462009177, 0.642259371967897, 0.955175660661444, 1.00909750957735] --> Cd = [0.00617285380994743, 0.00729426778019865, 0.0100194565543492, 0.014871080086931, 0.0185150448281248] real 0m2.708s user 0m2.235s sys 0m0.299s + status=0 + set +x ================================================= data/session03/02_xfoil_Analysis.py passed (as expected) ================================================= ================================================= 03_xfoil_AutoExec.py test; + python 03_xfoil_AutoExec.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... ==> Creating xfoilAIM ==> Setting analysis values ==> Retrieve analysis results --> Alpha = [0.0, 3.0, 5.0, 7.0, 8.0] --> Cl = [-3.53757485379788e-07, 0.377437462009177, 0.642259371967897, 0.955175660661444, 1.00909750957735] --> Cd = [0.00617285380994743, 0.00729426778019865, 0.0100194565543492, 0.014871080086931, 0.0185150448281248] real 0m2.297s user 0m2.075s sys 0m0.263s + status=0 + set +x ================================================= data/session03/03_xfoil_AutoExec.py passed (as expected) ================================================= ================================================= 04_xfoil_MultiAnalysis.py test; + python 04_xfoil_MultiAnalysis.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... ==> Creating xfoilAIM ==> Setting analysis values ==> Retrieve analysis results --> Alpha = [0.0, 3.0, 5.0, 7.0, 8.0] --> Cl = [-3.53757485379788e-07, 0.377437462009177, 0.642259371967897, 0.955175660661444, 1.00909750957735] --> Cd = [0.00617285380994743, 0.00729426778019865, 0.0100194565543492, 0.014871080086931, 0.0185150448281248] ==> Retrieve analysis results --> Alpha = [2.87619487667565e-06, 0.789686474042309, 1.18477801663685, 2.37671255179611, 3.18364393502677] --> Cl = [8.20895546206445e-17, 0.1, 0.150000000000232, 0.300000000000163, 0.4] --> Cd = [0.00617285381077468, 0.0062302134848261, 0.00630554753827264, 0.00680929883615267, 0.00747424244865481] real 0m3.014s user 0m2.703s sys 0m0.337s + status=0 + set +x ================================================= data/session03/04_xfoil_MultiAnalysis.py passed (as expected) ================================================= ================================================= 05_xfoil_Camber_Plot.py test; + python 05_xfoil_Camber_Plot.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... ==> Creating xfoilAIM ==> Setting analysis values ==> Retrieve analysis results. camber = 0.0 ==> Retrieve analysis results. camber = 0.01 ==> Retrieve analysis results. camber = 0.04 ==> Retrieve analysis results. camber = 0.07 ==> Plotting analysis results (close plot window to finish Python script /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/data/session03/05_xfoil_Camber_Plot.py:65: UserWarning: FigureCanvasAgg is non-interactive, and thus cannot be shown plt.show() real 0m10.795s user 0m9.041s sys 0m0.600s + status=0 + set +x ================================================= data/session03/05_xfoil_Camber_Plot.py passed (as expected) ================================================= ================================================= 05_xfoil_Camber.py test; + python 05_xfoil_Camber.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... ==> Creating xfoilAIM ==> Setting analysis values ==> Retrieve analysis results. camber = 0.0 ==> Retrieve analysis results. camber = 0.01 ==> Retrieve analysis results. camber = 0.04 ==> Retrieve analysis results. camber = 0.07 --> Cambers = [0.0, 0.01, 0.04, 0.07] --> Alpha = [[0.0, 1.0, 3.0], [0.0, 1.0, 3.0], [0.0, 1.0, 3.0], [0.0, 1.0]] --> Cl = [[-3.53757485379788e-07, 0.126697477361245, 0.377437462181301], [0.140339949737298, 0.266469023977218, 0.514670926888676], [0.554542727545582, 0.680708956698583, 0.940291957324466], [0.919771481558351, 1.03861131519064]] --> Cd = [[0.00617285380994743, 0.00627268560115741, 0.00729426778763049], [0.00625861871528587, 0.00622635244564028, 0.00706717658622408], [0.00787687247022662, 0.00739456756394001, 0.00782133651724137], [0.00972065010483813, 0.0101041953398965]] real 0m5.200s user 0m4.565s sys 0m0.504s + status=0 + set +x ================================================= data/session03/05_xfoil_Camber.py passed (as expected) ================================================= ================================================= 06_xfoil_CleanDirty.py test; + python 06_xfoil_CleanDirty.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... ==> Creating xfoilAIM 1. No Errors -------------------------------------------------------------------------------- ==> Setting alpha sequence ==> Running preAnalysis ==> Running xFoil...... ==> Running postAnalysis --> Cl = [-3.53757485379788e-07, 0.377437462009177, 0.642259371967897, 0.955175660661444, 1.00909750957735] 2. DIRTY AnalysisVal Error -------------------------------------------------------------------------------- ==> Setting new alpha sequence ==> Attempting to get Cl ==> CAPSError = CAPS_DIRTY: ================================================================================ ================================================================================ ==> Running preAnalysis ==> Running xFoil...... ==> Running postAnalysis ==> Attempting to get Cl --> Cl = 0.252764696628542 3. DIRTY GeometryVal Error -------------------------------------------------------------------------------- ==> Modifying camber ==> Attempting to get Cl ==> CAPSError = CAPS_DIRTY: ================================================================================ ================================================================================ ==> Running preAnalysis ==> Running xFoil...... ==> Running postAnalysis ==> Attempting to get Cl --> Cl = [1.03861130997165, 1.15325582947854] 4. DIRTY pre- but no postAnalysis Error -------------------------------------------------------------------------------- ==> Modifying Mach ==> Running preAnalysis but not running postAnalysis ==> Attempting to get Cl ==> CAPSError = CAPS_DIRTY: ================================================================================ ================================================================================ ==> Running xFoil...... ==> Running postAnalysis ==> Attempting to get Cl --> Cl = [0.967203918354729, 1.07899610948986] 5. CLEAN Error -------------------------------------------------------------------------------- ==> Running preAnalysis ==> CAPSError = CAPS_CLEAN: ================================================================================ ================================================================================ real 0m4.984s user 0m4.517s sys 0m0.490s + status=0 + set +x ================================================= data/session03/06_xfoil_CleanDirty.py passed (as expected) ================================================= ================================================= 07_masstran_f118_AIM.py test; + python 07_masstran_f118_AIM.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-B.csm"... ==> Geometry used by masstranAll instance with no capsIntent ==> Geometry used by Wing instance with capsIntent='wing' ==> Geometry used by Tail instance with capsIntent='tail' ==> Geometry used by WingFuse instance with capsIntent=['wing','fuse'] real 0m2.470s user 0m1.025s sys 0m1.162s + status=0 + set +x ================================================= data/session03/07_masstran_f118_AIM.py passed (as expected) ================================================= ================================================= 08_masstran_f118_Wing.py test; + python 08_masstran_f118_Wing.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-C.csm"... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing:faces, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input --> Mass = 14792888.88889 --> CG = [64.85254706407, 4.613994176513e-14, -3.914745293593] real 0m1.544s user 0m1.014s sys 0m0.537s + status=0 + set +x ================================================= data/session03/08_masstran_f118_Wing.py passed (as expected) ================================================= ================================================= 09_masstran_f118.py test; + python 09_masstran_f118.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-C.csm"... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - Madeupium No "materialType" specified for Material tuple Madeupium, defaulting to "Isotropic" Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 6 Property name - fuse:nose Property name - fuse:side Property name - fuse:tail Property name - htail:faces Property name - vtail:faces Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input -->Mass = 52825838.86801 -->CG = [91.69615213878, 9.02135549621e-15, 0.7254947287442] real 0m2.086s user 0m1.235s sys 0m0.755s + status=0 + set +x ================================================= data/session03/09_masstran_f118.py passed (as expected) ================================================= ================================================= 10_masstran_f118_journal.py test; + python 10_masstran_f118_journal.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ################################################################################ ==> First execution ==> Loading geometry from file "f118-C.csm"... ================================================================================ ==> Computing mass 1 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing:faces, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 488 Number of elements = 972 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 972 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input --> 14792888.88889 Something went wrong! ################################################################################ ==> Second execution ==> Loading geometry from file "f118-C.csm"... ================================================================================ ==> Computing mass 1 --> 14792888.88889 CAPS Info: Hit last success -- going live! ================================================================================ ==> Computing mass 2 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing:faces, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 488 Number of elements = 972 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 972 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input --> 1479288.888889 Something went wrong! ################################################################################ ==> Third execution ==> Loading geometry from file "f118-C.csm"... ================================================================================ ==> Computing mass 1 --> 14792888.88889 ================================================================================ ==> Computing mass 2 --> 1479288.888889 CAPS Info: Hit last success -- going live! ================================================================================ ==> Computing mass 3 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing:faces, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 488 Number of elements = 972 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 972 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input --> 147928.8888889 ################################################################################ ==> Fourth execution ==> Loading geometry from file "f118-C.csm"... ================================================================================ ==> Computing mass 1 --> 14792888.88889 ================================================================================ ==> Computing mass 2 --> 1479288.888889 ================================================================================ ==> Computing mass 3 --> 147928.8888889 real 0m1.929s user 0m1.180s sys 0m0.708s + status=0 + set +x ================================================= data/session03/10_masstran_f118_journal.py passed (as expected) ================================================= ================================================= + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log + echo 'f118-C.csm test;' f118-C.csm test; + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log + /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveESP -batch -verify -outLevel 0 f118-C.csm WARNING:: cannot open "./verify_7.8.1/f118-C.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.122s user 0m0.085s sys 0m0.039s + status=0 + set +x ================================================= solutions/session03/f118-C passed (as expected) ================================================= ================================================= xfoil_thickness.py test; + python xfoil_thickness.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/session03/naca.csm"... ==> Create xfoilAIM ==> Setting analysis values ==> Retrieve analysis results ==> Retrieve analysis results ==> Retrieve analysis results ==> Retrieve analysis results --> Thickness = [0.08, 0.1, 0.12, 0.16] --> Alpha = [[0.0, 1.0, 3.0], [0.0, 1.0, 3.0], [0.0, 1.0, 3.0], [0.0, 1.0, 3.0]] --> Cl = [[4.33419511114853e-07, 0.118003705247099, 0.407823091300777], [3.88197201209935e-07, 0.123993123613511, 0.371340021266889], [-3.53757485379788e-07, 0.126697477361245, 0.377437462181301], [-2.73508054507172e-07, 0.127624902798225, 0.38086778943914]] --> Cd = [[0.00449613835213644, 0.00482192214519885, 0.00769709940290386], [0.00540044826496712, 0.00554773736538764, 0.00718424709042918], [0.00617285380994743, 0.00627268560115741, 0.00729426778763049], [0.00752780925540312, 0.00759373202201033, 0.00822814692467068]] real 0m3.430s user 0m2.858s sys 0m0.477s + status=0 + set +x ================================================= solutions/session03/xfoil_thickness.py passed (as expected) ================================================= ================================================= f118_masstran.py test; + python f118_masstran.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/session03/f118-B.csm"... ==> Geometry with capsIntent=['wing','fuse', 'htail'] real 0m1.322s user 0m0.913s sys 0m0.476s + status=0 + set +x ================================================= solutions/session03/f118_masstran.py passed (as expected) ================================================= ================================================= masstran_topbot.py test; + python masstran_topbot.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-C.csm"... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - Madeupium No "materialType" specified for Material tuple Madeupium, defaulting to "Isotropic" Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 8 Property name - fuse:bottom Property name - fuse:nose Property name - fuse:side Property name - fuse:tail Property name - fuse:top Property name - htail:faces Property name - vtail:faces Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input -->Mass = 52073438.86801 -->CG = [91.72065954403, 0.04009689171826, 0.1932821772294] real 0m1.574s user 0m0.960s sys 0m0.622s + status=0 + set +x ================================================= solutions/session03/masstran_topbot.py passed (as expected) ================================================= ================================================= masstran_CG.py test; + python masstran_CG.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "f118-C.csm"... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - Madeupium No "materialType" specified for Material tuple Madeupium, defaulting to "Isotropic" Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 8 Property name - fuse:bottom Property name - fuse:nose Property name - fuse:side Property name - fuse:tail Property name - fuse:top Property name - htail:faces Property name - vtail:faces Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input -->Oringal CG = 91.72065954403 -->CG sweep = [84.05056882825, 85.58458697141, 87.11860511456, 88.65262325772, 90.18664140087, 91.72065954403, 93.25467768718, 94.78869583034, 96.32271397349, 97.85673211665, 99.3907502598] real 0m2.513s user 0m1.451s sys 0m1.144s + status=0 + set +x ================================================= solutions/session03/masstran_CG.py passed (as expected) ================================================= ================================================= + echo 'f118-D.csm test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log f118-D.csm test; + /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveESP -batch -verify -outLevel 0 f118-D.csm + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.8.1/f118-D.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.095s user 0m0.075s sys 0m0.022s + status=0 + set +x ================================================= data/session04/f118-D passed (as expected) ================================================= ================================================= + echo 'naca.csm test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log naca.csm test; + /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveESP -batch -verify -outLevel 0 naca.csm + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.8.1/naca.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.106s user 0m0.072s sys 0m0.022s + status=0 + set +x ================================================= data/session04/naca passed (as expected) ================================================= ================================================= 1_mses_Deriv.py test; + python 1_mses_Deriv.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... ==> Area and Area derivatives... --> Area 0.08221896898506213 --> dArea/dthick 0.6847211877073475 ==> Drag and Drag derivatives... Getting CFD design variables....... Number of design variables - 2 Design Variable name - camber Design Variable name - thick Done getting CFD design variables --> CD = 0.005288406846931541 --> dCD/dAlpha = -2.942742400634222e-07 --> dCD/dMach = 0.0012453361427576114 --> dCD/dcamber = -3.160438517971385e-05 --> dCD/dthick = 0.01572064644523116 ==> All Drag derivatives... --> CD derivs = {'Alpha': -2.942742400634222e-07, 'Mach': 0.0012453361427576114, 'Re': -3.6387781085334707e-11, 'camber': -3.160438517971385e-05, 'thick': 0.01572064644523116} real 0m4.754s user 0m3.864s sys 0m0.449s + status=0 + set +x ================================================= data/session04/1_mses_Deriv.py passed (as expected) ================================================= ================================================= 2_mses_DerivPlot_CD_Alpha.py test; + python 2_mses_DerivPlot_CD_Alpha.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... --> Alpha -3.0 --> Alpha -2.5714285714285716 --> Alpha -2.142857142857143 --> Alpha -1.7142857142857144 --> Alpha -1.2857142857142858 --> Alpha -0.8571428571428572 --> Alpha -0.4285714285714288 --> Alpha 0.0 --> Alpha 0.4285714285714284 --> Alpha 0.8571428571428568 --> Alpha 1.2857142857142856 --> Alpha 1.7142857142857144 --> Alpha 2.1428571428571423 --> Alpha 2.571428571428571 --> Alpha 3.0 /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/data/session04/2_mses_DerivPlot_CD_Alpha.py:77: UserWarning: FigureCanvasAgg is non-interactive, and thus cannot be shown plt.show() real 0m47.916s user 0m44.644s sys 0m2.240s + status=0 + set +x ================================================= data/session04/2_mses_DerivPlot_CD_Alpha.py passed (as expected) ================================================= ================================================= 3_mses_OpenMDAO_CD_Alpha.py test; + python 3_mses_OpenMDAO_CD_Alpha.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log [macys-VM:47182] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/3808821248/sm_segment.macys-VM.502.e3060000.0 could be created. ==> Starting Optimization... --> Alpha [3.] --> CD [0.00803595] --> Alpha [3.] --> CD [0.00803595] --> Alpha [3.] --> CD_alpha [[0.00014124]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 1 M = 10 At X0 0 variables are exactly at the bounds At iterate 0 f= 8.03595D-03 |proj g|= 1.41235D-04 --> Alpha [2.99985876] --> CD [0.00803593] --> Alpha [2.99985876] --> CD_alpha [[0.00014123]] At iterate 1 f= 8.03593D-03 |proj g|= 1.41231D-04 --> Alpha [-1.95868784] --> CD [0.00791991] --> Alpha [-1.95868784] --> CD_alpha [[-8.82295429e-05]] At iterate 2 f= 7.91991D-03 |proj g|= 8.82295D-05 --> Alpha [-0.05208413] --> CD [0.00783466] --> Alpha [-0.05208413] --> CD_alpha [[-2.58049269e-06]] At iterate 3 f= 7.83466D-03 |proj g|= 2.58049D-06 --> Alpha [0.00535932] --> CD [0.0078346] --> Alpha [0.00535932] --> CD_alpha [[1.70395921e-08]] At iterate 4 f= 7.83460D-03 |proj g|= 1.70396D-08 --> Alpha [0.00498249] --> CD [0.0078346] --> Alpha [0.00498249] --> CD_alpha [[-2.03053106e-09]] At iterate 5 f= 7.83460D-03 |proj g|= 2.03053D-09 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 1 5 6 5 0 0 2.031D-09 7.835D-03 F = 7.8346002301430146E-003 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- --> Optimized value: [0.00498249] real 0m33.433s user 0m20.255s sys 0m1.817s + status=0 + set +x ================================================= data/session04/3_mses_OpenMDAO_CD_Alpha.py passed (as expected) ================================================= ================================================= 4_mses_DerivPlot_CD_camber.py test; + python 4_mses_DerivPlot_CD_camber.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... --> camber -0.1 Getting CFD design variables....... Number of design variables - 1 Design Variable name - camber Done getting CFD design variables --> camber -0.08571428571428572 --> camber -0.07142857142857142 --> camber -0.05714285714285715 --> camber -0.04285714285714286 --> camber -0.028571428571428567 --> camber -0.01428571428571429 --> camber 0.0 --> camber 0.01428571428571429 --> camber 0.02857142857142858 --> camber 0.04285714285714287 --> camber 0.05714285714285716 --> camber 0.07142857142857142 --> camber 0.08571428571428572 --> camber 0.1 /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/data/session04/4_mses_DerivPlot_CD_camber.py:80: UserWarning: FigureCanvasAgg is non-interactive, and thus cannot be shown plt.show() real 0m55.100s user 0m48.747s sys 0m3.051s + status=0 + set +x ================================================= data/session04/4_mses_DerivPlot_CD_camber.py passed (as expected) ================================================= ================================================= 5_mses_OpenMDAO_CD_camber.py test; + python 5_mses_OpenMDAO_CD_camber.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log [macys-VM:47344] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/2722234368/sm_segment.macys-VM.502.a2420000.0 could be created. ==> Starting Optimization... --> camber [0.1] Getting CFD design variables....... Number of design variables - 1 Design Variable name - camber Done getting CFD design variables --> CD [0.01370217] --> camber [0.1] --> CD [0.01370217] --> camber [0.1] --> CD_camber [[0.17593484]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 1 M = 10 At X0 1 variables are exactly at the bounds At iterate 0 f= 1.37022D-02 |proj g|= 1.75935D-01 --> camber [-0.07593484] --> CD [0.01053685] --> camber [-0.07593484] --> CD_camber [[-0.07712955]] At iterate 1 f= 1.05368D-02 |proj g|= 7.71296D-02 --> camber [-0.02231302] --> CD [0.00803517] --> camber [-0.02231302] --> CD_camber [[-0.01711041]] At iterate 2 f= 8.03517D-03 |proj g|= 1.71104D-02 --> camber [-0.00702637] --> CD [0.00785371] --> camber [-0.00702637] --> CD_camber [[-0.00523687]] At iterate 3 f= 7.85371D-03 |proj g|= 5.23687D-03 --> camber [-0.00028414] --> CD [0.00783469] --> camber [-0.00028414] --> CD_camber [[-0.00015021]] At iterate 4 f= 7.83469D-03 |proj g|= 1.50214D-04 --> camber [-8.50372178e-05] --> CD [0.00783469] --> camber [-8.50372178e-05] --> CD_camber [[-1.22615302e-06]] At iterate 5 f= 7.83469D-03 |proj g|= 1.22615D-06 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 1 5 6 5 0 0 1.226D-06 7.835D-03 F = 7.8346852164040588E-003 CONVERGENCE: NORM_OF_PROJECTED_GRADIENT_<=_PGTOL Optimization Complete ----------------------------------- --> Optimized value: [-8.50372178e-05] real 0m25.781s user 0m21.265s sys 0m1.822s + status=0 + set +x ================================================= data/session04/5_mses_OpenMDAO_CD_camber.py passed (as expected) ================================================= ================================================= 6_mses_DerivPlot_CL2_camber.py test; + python 6_mses_DerivPlot_CL2_camber.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... --> camber -0.1 Getting CFD design variables....... Number of design variables - 1 Design Variable name - camber Done getting CFD design variables --> camber -0.08571428571428572 --> camber -0.07142857142857142 --> camber -0.05714285714285715 --> camber -0.04285714285714286 --> camber -0.028571428571428567 --> camber -0.01428571428571429 --> camber 0.0 --> camber 0.01428571428571429 --> camber 0.02857142857142858 --> camber 0.04285714285714287 --> camber 0.05714285714285716 --> camber 0.07142857142857142 --> camber 0.08571428571428572 --> camber 0.1 /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/data/session04/6_mses_DerivPlot_CL2_camber.py:82: UserWarning: FigureCanvasAgg is non-interactive, and thus cannot be shown plt.show() real 0m50.548s user 0m47.177s sys 0m2.446s + status=0 + set +x ================================================= data/session04/6_mses_DerivPlot_CL2_camber.py passed (as expected) ================================================= ================================================= 7_mses_OpenMDAO_CL2_camber.py test; + python 7_mses_OpenMDAO_CL2_camber.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log [macys-VM:47516] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/3907649536/sm_segment.macys-VM.502.e8ea0000.0 could be created. ==> Starting Optimization... --> camber [0.1] Getting CFD design variables....... Number of design variables - 1 Design Variable name - camber Done getting CFD design variables --> CL2 [1.23491816] --> camber [0.1] --> CL2 [1.23491816] --> camber [0.1] --> CL2_camber [[14.37226759]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 1 M = 10 At X0 1 variables are exactly at the bounds At iterate 0 f= 1.23492D+00 |proj g|= 2.00000D-01 --> camber [-0.1] --> CL2 [1.23490173] --> camber [-0.1] --> CL2_camber [[-14.37230183]] --> camber [9.92558193e-05] --> CL2 [1.68716435e-06] --> camber [9.92558193e-05] --> CL2_camber [[0.03422627]] At iterate 1 f= 1.68716D-06 |proj g|= 3.42263D-02 --> camber [-0.00013922] --> CL2 [3.35684832e-06] --> camber [-0.00013922] --> CL2_camber [[-0.04827804]] --> camber [2.46989211e-07] --> CL2 [1.06678519e-12] --> camber [2.46989211e-07] --> CL2_camber [[-2.72158112e-05]] At iterate 2 f= 1.06679D-12 |proj g|= 2.72158D-05 --> camber [3.2565583e-07] --> CL2 [1.06525442e-14] --> camber [3.2565583e-07] --> CL2_camber [[2.71962989e-06]] At iterate 3 f= 1.06525D-14 |proj g|= 2.71963D-06 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 1 3 6 3 0 0 2.720D-06 1.065D-14 F = 1.0652544204695267E-014 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- --> Optimized value: [3.2565583e-07] real 0m24.559s user 0m20.945s sys 0m1.929s + status=0 + set +x ================================================= data/session04/7_mses_OpenMDAO_CL2_camber.py passed (as expected) ================================================= ================================================= 8_mses_OpenMDAO_CDCL.py test; + python 8_mses_OpenMDAO_CDCL.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log [macys-VM:47573] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/4132700160/sm_segment.macys-VM.502.f6540000.0 could be created. ==> Starting Optimization... --> Alpha [0.] --> camber [0.1] Getting CFD design variables....... Number of design variables - 1 Design Variable name - camber Done getting CFD design variables --> CD [0.01370217] --> CL [1.11126872] --> Alpha [0.] --> camber [0.1] --> CD [0.01370217] --> CL [1.11126872] --> Alpha [0.] --> camber [0.1] --> CD_Alpha [[0.00105841]] --> CL_Alpha [[0.09897644]] --> CD_camber [[0.17593484]] --> CL_camber [[6.46660315]] --> Alpha [0.00077914] --> camber [0.04412123] --> CD [0.00864297] --> CL [0.57037493] --> Alpha [0.00077914] --> camber [0.04412123] --> CD_Alpha [[0.00023874]] --> CL_Alpha [[0.12984116]] --> CD_camber [[0.03642554]] --> CL_camber [[12.53395276]] --> Alpha [0.00103084] --> camber [0.0584497] --> CD [0.00930221] --> CL [0.74439506] --> Alpha [0.00103084] --> camber [0.0584497] --> CD_Alpha [[0.00033987]] --> CL_Alpha [[0.12673085]] --> CD_camber [[0.05177185]] --> CL_camber [[11.83400798]] --> Alpha [0.00125705] --> camber [0.05892091] --> CD [0.00932812] --> CL [0.74994585] Optimization terminated successfully (Exit mode 0) Current function value: 0.009328118059401761 Iterations: 3 Function evaluations: 4 Gradient evaluations: 3 Optimization Complete ----------------------------------- --> Optimized value: [0.05892091] real 0m18.887s user 0m15.463s sys 0m1.441s + status=0 + set +x ================================================= data/session04/8_mses_OpenMDAO_CDCL.py passed (as expected) ================================================= ================================================= 9_masstran_OpenMDAO_thick.py test; + python 9_masstran_OpenMDAO_thick.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log [macys-VM:47618] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/2159083520/sm_segment.macys-VM.502.80b10000.0 could be created. ==> Starting Optimization... /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/Python-3.11.9/lib/python3.11/site-packages/openmdao/core/driver.py:619: DriverWarning:The following design variable initial conditions are out of their specified bounds: masstranSystem.x2 val: [0.] lower: 0.01 upper: 10.0 Set the initial value of the design variable to a valid value or set the driver option['invalid_desvar_behavior'] to 'ignore'. --> x1 [0.1] --> x2 [0.] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuse Property name - htail Property name - vtail Property name - wing Done getting FEA properties Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [2.75695334] --> x1 [0.1] --> x2 [0.01] /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/data/session04/9_masstran_OpenMDAO_thick.py:52: DeprecationWarning: Conversion of an array with ndim > 0 to a scalar is deprecated, and will error in future. Ensure you extract a single element from your array before performing this operation. (Deprecated NumPy 1.25.) "x1": {"initialValue":float(inputs['x1'])}, /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/data/session04/9_masstran_OpenMDAO_thick.py:53: DeprecationWarning: Conversion of an array with ndim > 0 to a scalar is deprecated, and will error in future. Ensure you extract a single element from your array before performing this operation. (Deprecated NumPy 1.25.) "x2": {"initialValue":float(inputs['x2'])}, Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [2.70119648] --> x1 [0.1] --> x2 [0.01] --> dCGx_x1 [[-68.82272937]] --> dCGx_x2 [[-5.53091882]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 2 M = 10 At X0 1 variables are exactly at the bounds At iterate 0 f= 2.70120D+00 |proj g|= 9.90000D+00 --> x1 [10.] --> x2 [5.54091882] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [10.16370853] --> x1 [10.] --> x2 [5.54091882] --> dCGx_x1 [[0.04843981]] --> dCGx_x2 [[0.03754845]] --> x1 [3.33378327] --> x2 [1.81664573] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [8.85443326] --> x1 [3.33378327] --> x2 [1.81664573] --> dCGx_x1 [[0.48418692]] --> dCGx_x2 [[0.1268106]] --> x1 [1.12760341] --> x2 [0.5841001] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [5.7972651] --> x1 [1.12760341] --> x2 [0.5841001] --> dCGx_x1 [[3.182136]] --> dCGx_x2 [[0.42790152]] --> x1 [0.42334159] --> x2 [0.19064405] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [1.60230885] --> x1 [0.42334159] --> x2 [0.19064405] --> dCGx_x1 [[8.88674345]] --> dCGx_x2 [[0.86253194]] At iterate 1 f= 1.60231D+00 |proj g|= 4.13342D-01 --> x1 [0.38612876] --> x2 [0.16914154] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [1.24954556] --> x1 [0.38612876] --> x2 [0.16914154] --> dCGx_x1 [[9.04121089]] --> dCGx_x2 [[0.8599867]] --> x1 [0.23727742] --> x2 [0.08313149] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [0.04927766] --> x1 [0.23727742] --> x2 [0.08313149] --> dCGx_x1 [[3.58807069]] --> dCGx_x2 [[0.31359947]] At iterate 2 f= 4.92777D-02 |proj g|= 2.27277D-01 --> x1 [0.11213433] --> x2 [0.01347811] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [1.95060563] --> x1 [0.11213433] --> x2 [0.01347811] --> dCGx_x1 [[-52.76118222]] --> dCGx_x2 [[-4.27221829]] --> x1 [0.21361795] --> x2 [0.06996287] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [5.61440048e-05] --> x1 [0.21361795] --> x2 [0.06996287] --> dCGx_x1 [[0.13868009]] --> dCGx_x2 [[0.01195172]] At iterate 3 f= 5.61440D-05 |proj g|= 1.38680D-01 --> x1 [0.21266725] --> x2 [0.06943529] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [3.06804662e-06] --> x1 [0.21266725] --> x2 [0.06943529] --> dCGx_x1 [[-0.03260179]] --> dCGx_x2 [[-0.00280809]] At iterate 4 f= 3.06805D-06 |proj g|= 3.26018D-02 --> x1 [0.2128482] --> x2 [0.0695357] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [1.43517333e-10] --> x1 [0.2128482] --> x2 [0.0695357] --> dCGx_x1 [[0.00022274]] --> dCGx_x2 [[1.91872562e-05]] At iterate 5 f= 1.43517D-10 |proj g|= 2.22739D-04 --> x1 [0.21284697] --> x2 [0.06953502] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [3.63550505e-16] --> x1 [0.21284697] --> x2 [0.06953502] --> dCGx_x1 [[3.54510824e-07]] --> dCGx_x2 [[3.05383747e-08]] At iterate 6 f= 3.63551D-16 |proj g|= 3.54511D-07 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 2 6 12 7 0 0 3.545D-07 3.636D-16 F = 3.6355050512987024E-016 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- ==> Optimized value: --> x1 [0.21284697] --> x2 [0.06953502] real 0m5.831s user 0m3.262s sys 0m1.686s + status=0 + set +x ================================================= data/session04/9_masstran_OpenMDAO_thick.py passed (as expected) ================================================= ================================================= masstran_OpenMDAO_geom.py test; + python masstran_OpenMDAO_geom.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log [macys-VM:47664] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/129499136/sm_segment.macys-VM.502.7b80000.0 could be created. ==> Initial values: htail:lh 5.0 wing:xroot 4.0 ==> Starting Optimization... --> htail:lh [5.] --> wing:xroot [4.] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuse Property name - htail Property name - vtail Property name - wing Done getting FEA properties Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [2.10539929] --> htail:lh [5.] --> wing:xroot [4.] --> dCGx [2.10539929] --> htail:lh [5.] --> wing:xroot [4.] --> dCGx_htail:lh [[-0.40374365]] --> dCGx_wing:xroot [[-1.15229479]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 2 M = 10 At X0 0 variables are exactly at the bounds At iterate 0 f= 2.10540D+00 |proj g|= 1.15229D+00 --> htail:lh [5.40374365] --> wing:xroot [5.15229479] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [0.86918465] --> htail:lh [5.40374365] --> wing:xroot [5.15229479] --> dCGx_htail:lh [[-0.30002756]] --> dCGx_wing:xroot [[-0.74124931]] At iterate 1 f= 8.69185D-01 |proj g|= 7.41249D-01 --> htail:lh [6.474753] --> wing:xroot [7.25471671] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [0.00905292] --> htail:lh [6.474753] --> wing:xroot [7.25471671] --> dCGx_htail:lh [[0.03711399]] --> dCGx_wing:xroot [[0.07531706]] At iterate 2 f= 9.05292D-03 |proj g|= 7.53171D-02 --> htail:lh [6.35917671] --> wing:xroot [7.05983716] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [1.94377289e-05] --> htail:lh [6.35917671] --> wing:xroot [7.05983716] --> dCGx_htail:lh [[-0.00169617]] --> dCGx_wing:xroot [[-0.00349307]] At iterate 3 f= 1.94377D-05 |proj g|= 3.49307D-03 --> htail:lh [6.3642348] --> wing:xroot [7.06847132] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [2.31615861e-10] --> htail:lh [6.3642348] --> wing:xroot [7.06847132] --> dCGx_htail:lh [[-5.85873617e-06]] --> dCGx_wing:xroot [[-1.20573655e-05]] At iterate 4 f= 2.31616D-10 |proj g|= 1.20574D-05 --> htail:lh [6.36425233] --> wing:xroot [7.06850123] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [6.3756283e-18] --> htail:lh [6.36425233] --> wing:xroot [7.06850123] --> dCGx_htail:lh [[9.72035735e-10]] --> dCGx_wing:xroot [[2.00045928e-09]] At iterate 5 f= 6.37563D-18 |proj g|= 2.00046D-09 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 2 5 6 5 0 0 2.000D-09 6.376D-18 F = 6.3756282976940919E-018 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- ==> Optimized values: --> htail:lh 6.364252334270465 --> wing:xroot 7.06850122864588 real 0m4.442s user 0m3.350s sys 0m1.168s + status=0 + set +x ================================================= solutions/session04/masstran_OpenMDAO_geom.py passed (as expected) ================================================= ================================================= + echo 'avlPlaneVanilla.csm test;' + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log avlPlaneVanilla.csm test; + /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveESP -batch -verify -outLevel 0 avlPlaneVanilla.csm + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.8.1/avlPlaneVanilla.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.410s user 0m0.326s sys 0m0.032s + status=0 + set +x ================================================= data/session06/avlPlaneVanilla passed (as expected) ================================================= ================================================= 1_avl_PlaneVanilla.py test; + python 1_avl_PlaneVanilla.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "avlPlaneVanilla.csm"... ==> Viewing Plane Vanilla bodies... ==> Create avlAIM ==> Viewing AVL Plane Vanilla bodies... ==> Setting analysis values Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Warning: Control Elevator not found in controls tuple! Only defaults will be used. Warning: Control Elevator not found in controls tuple! Only defaults will be used. Warning: Control Elevator not found in controls tuple! Only defaults will be used. Warning: Control Rudder not found in controls tuple! Only defaults will be used. Warning: Control Rudder not found in controls tuple! Only defaults will be used. Warning: Control AileronRight not found in controls tuple! Only defaults will be used. Warning: Control AileronLeft not found in controls tuple! Only defaults will be used. Warning: Control AileronRight not found in controls tuple! Only defaults will be used. Warning: Control AileronLeft not found in controls tuple! Only defaults will be used. Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 1) Control surface 1 of 1 Section 2 of 3 (ID = 0) Control surface 1 of 1 Section 3 of 3 (ID = 2) Control surface 1 of 1 Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Control surface 1 of 1 Section 2 of 2 (ID = 0) Control surface 1 of 1 Writing surface - Wing (ID = 2) Section 1 of 3 (ID = 1) Control surface 1 of 1 Section 2 of 3 (ID = 0) Control surface 1 of 2 Control surface 2 of 2 Section 3 of 3 (ID = 2) Control surface 1 of 1 --> CLtot = 0.5813612009207021 --> CDtot = 0.006414738598480186 --> CDind = 0.006414738598480186 --> e = 0.9155417145048191 real 0m2.313s user 0m1.330s sys 0m0.908s + status=0 + set +x ================================================= data/session06/1_avl_PlaneVanilla.py passed (as expected) ================================================= ================================================= 2_avl_PlaneVanillaControl.py test; + python 2_avl_PlaneVanillaControl.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "avlPlaneVanilla.csm"... ==> Creating avlAIM ==> Setting analysis values ==> Some stability derivatives (old) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice control surface data VLM control surface name - AileronLeft VLM control surface name - AileronRight VLM control surface name - Elevator VLM control surface name - Rudder Done getting vortex lattice control surface data Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 1) Control surface 1 of 1 Section 2 of 3 (ID = 0) Control surface 1 of 1 Section 3 of 3 (ID = 2) Control surface 1 of 1 Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Control surface 1 of 1 Section 2 of 2 (ID = 0) Control surface 1 of 1 Writing surface - Wing (ID = 2) Section 1 of 3 (ID = 1) Control surface 1 of 1 Section 2 of 3 (ID = 0) Control surface 1 of 2 Control surface 2 of 2 Section 3 of 3 (ID = 2) Control surface 1 of 1 --> CLa = 6.186807004016531 --> CLb = 0.06076552936219984 --> CLp' = 0.07726884267630249 --> CLq' = 11.77186898082121 --> CLr' = 0.9883703770411724 --> dCL/dAileronRight = 0.02247452142342 --> dCL/dAileronLeft = 0.0225246749619 --> dCL/dElevator = 0.005432144424888 --> dCL/dRudder = -2.654019499439e-06 ==> Some stability derivatives (new) --> dCL/dAlpha = 6.186807004016531 --> dCL/dBeta = 0.06076552936219984 --> dCL/dp' = 0.07726884267630249 --> dCL/dq' = 11.77186898082121 --> dCL/dr' = 0.9883703770411724 --> dCL/dAileronRight = 0.02247452142342404 --> dCL/dAileronLeft = 0.02252467496190029 --> dCL/dElevator = 0.005432144424888405 --> dCL/dRudder = -2.654019499439076e-06 real 0m2.133s user 0m1.295s sys 0m0.911s + status=0 + set +x ================================================= data/session06/2_avl_PlaneVanillaControl.py passed (as expected) ================================================= ================================================= 3_avl_TransportGeom.py test; + python 3_avl_TransportGeom.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Viewing transport bodies... MESSAGE:: Building wingOml MESSAGE:: Building wingHinges MESSAGE:: Building htailOml MESSAGE:: Building htailHinges MESSAGE:: Building vtailOml MESSAGE:: Building vtailHinges ==> Create AVL aim... ==> Viewing avl bodies... real 0m19.885s user 0m21.657s sys 0m8.218s + status=0 + set +x ================================================= data/session06/3_avl_TransportGeom.py passed (as expected) ================================================= ================================================= 4_avl_TransportControl.py test; + python 4_avl_TransportControl.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Creating AVL aim... MESSAGE:: Building wingOml MESSAGE:: Building wingHinges MESSAGE:: Building htailOml MESSAGE:: Building htailHinges MESSAGE:: Building vtailOml MESSAGE:: Building vtailHinges Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice control surface data VLM control surface name - HtailControl_1 VLM control surface name - VtailControl_1 VLM control surface name - WingControl_1 VLM control surface name - WingControl_2 VLM control surface name - WingControl_3 VLM control surface name - WingControl_4 Done getting vortex lattice control surface data Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control VtailControl1 not found in controls tuple! Only defaults will be used. Warning: Control VtailControl1 not found in controls tuple! Only defaults will be used. Warning: Control WingControl1 not found in controls tuple! Only defaults will be used. Warning: Control WingControl1 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl4 not found in controls tuple! Only defaults will be used. Warning: Control WingControl4 not found in controls tuple! Only defaults will be used. Writing surface - Htail (ID = 0) Section 1 of 7 (ID = 0) Section 2 of 7 (ID = 3) Control surface 1 of 1 Section 3 of 7 (ID = 4) Control surface 1 of 1 Section 4 of 7 (ID = 1) Section 5 of 7 (ID = 5) Control surface 1 of 1 Section 6 of 7 (ID = 6) Control surface 1 of 1 Section 7 of 7 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 4 (ID = 1) Section 2 of 4 (ID = 3) Control surface 1 of 1 Section 3 of 4 (ID = 2) Control surface 1 of 1 Section 4 of 4 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 17 (ID = 0) Section 2 of 17 (ID = 5) Control surface 1 of 1 Section 3 of 17 (ID = 6) Control surface 1 of 1 Section 4 of 17 (ID = 7) Control surface 1 of 1 Section 5 of 17 (ID = 8) Control surface 1 of 1 Section 6 of 17 (ID = 4) Section 7 of 17 (ID = 9) Control surface 1 of 1 Section 8 of 17 (ID = 10) Control surface 1 of 1 Section 9 of 17 (ID = 1) Section 10 of 17 (ID = 11) Control surface 1 of 1 Section 11 of 17 (ID = 12) Control surface 1 of 1 Section 12 of 17 (ID = 3) Section 13 of 17 (ID = 13) Control surface 1 of 1 Section 14 of 17 (ID = 14) Control surface 1 of 1 Section 15 of 17 (ID = 15) Control surface 1 of 1 Section 16 of 17 (ID = 16) Control surface 1 of 1 Section 17 of 17 (ID = 2) ==> Some stability derivatives --> CLa = 5.329631112234144 --> CLb = 1.651864185398326e-09 --> CLp' = -4.001376233674891e-10 --> CLq' = 28.72846790224948 --> CLr' = -2.767805233677674e-09 --> Xcg = 55.4263 --> Xnp = 91.29113415652209 --> StaticMargin = 1.6523694366308268 --> htailControl1 {'CLtot': 0.008154370285814, 'CYtot': 9.075194510381e-11, "Cl'tot": 4.489035946149e-12, 'Cmtot': -0.03748884222584, "Cn'tot": -5.410997993488e-11, 'CDff': 0.001133243689262, 'e': -0.003225847672438} --> VtailControl1 {'CLtot': -3.031950282476e-11, 'CYtot': 0.001746902748416, "Cl'tot": 0.0001578887965311, 'Cmtot': 1.479167618946e-10, "Cn'tot": -0.0009155267170673, 'CDff': 3.05051259299e-13, 'e': -4.238167293539e-12} --> WingControl1 {'CLtot': 0.002454272406152, 'CYtot': 0.0001047561437285, "Cl'tot": 0.0008699288714632, 'Cmtot': -0.006084028398663, "Cn'tot": 0.0001105826995691, 'CDff': 4.762256182255e-05, 'e': 0.002671723839937} --> WingControl2 {'CLtot': 0.008875217411974, 'CYtot': 6.234219060462e-12, "Cl'tot": 8.928483522817e-14, 'Cmtot': -0.01681584091322, "Cn'tot": -3.519260150842e-12, 'CDff': 0.000369541483347, 'e': 0.007231131090133} --> WingControl3 {'CLtot': 0.005956182097902, 'CYtot': -1.9932307583e-11, "Cl'tot": -5.706407696973e-13, 'Cmtot': -0.005500424200486, "Cn'tot": 1.166099661329e-11, 'CDff': 0.0007054644635254, 'e': -0.0007874262943396} --> WingControl4 {'CLtot': 0.002454272405997, 'CYtot': -0.0001047561404806, "Cl'tot": -0.0008699288714121, 'Cmtot': -0.00608402839677, "Cn'tot": -0.0001105827014567, 'CDff': 4.762256175753e-05, 'e': 0.002671723841347} real 0m22.875s user 0m22.396s sys 0m7.930s + status=0 + set +x ================================================= data/session06/4_avl_TransportControl.py passed (as expected) ================================================= ================================================= 5_avl_TransportEigen.py test; + python 5_avl_TransportEigen.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Create AVL aim... ==> Running Analysis MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Writing mass properties file: caps.mass Parsing MassProp Note: The following floating-point exceptions are signalling: IEEE_DIVIDE_BY_ZERO ==> Outputs --> Xcg = 89.3122 meter --> Xnp = 92.43912770212773 meter --> StaticMargin = 0.47265167768451544 --> EigenValues {'case 1': [[-3.1240286, 0.0], [0.01975706, 0.97330897], [0.01975706, -0.97330897], [-0.013027091, 0.0], [-0.32616585, 0.92439209], [-0.32616585, -0.92439209], [-0.013243773, 0.13183873], [-0.013243773, -0.13183873]]} --> Real Eigen Values = [-3.1240286, 0.01975706, 0.01975706, -0.013027091, -0.32616585, -0.32616585, -0.013243773, -0.013243773] real 0m8.274s user 0m5.994s sys 0m3.225s + status=0 + set +x ================================================= data/session06/5_avl_TransportEigen.py passed (as expected) ================================================= ================================================= 6_avl_masstran_Geom.py test; + python 6_avl_masstran_Geom.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Vewing AVL geometry MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml ==> Vewing Masstran geometry real 0m7.165s user 0m5.303s sys 0m3.715s + status=0 + set +x ================================================= data/session06/6_avl_masstran_Geom.py passed (as expected) ================================================= ================================================= 7_avl_masstran_Eigen.py test; + python 7_avl_masstran_Eigen.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Creating masstran aim... ==> Creating AVL aim... ==> Running Analysis MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wingSkin, index = 1 Name = fuseSkin, index = 2 Name = htailSkin, index = 3 Name = vtailSkin, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 5460 Number of elements = 10916 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 10916 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 4599 Number of elements = 9194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 9194 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2722 Number of elements = 5440 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 5440 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 18403 Combined Number of elements = 36790 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 36790 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuseSkin Property name - htailSkin Property name - vtailSkin Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Writing mass properties file: caps.mass Parsing MassProp Note: The following floating-point exceptions are signalling: IEEE_DIVIDE_BY_ZERO ==> Outputs --> Xcg = 89.6946 meter --> Xnp = 92.4242670979591 meter --> StaticMargin = 0.41260363406953277 --> EigenValues {'case 1': [[-0.70465113, 0.0], [0.13846754, 0.5514659], [0.13846754, -0.5514659], [-0.1614276, 0.51358138], [-0.1614276, -0.51358138], [-0.0068180511, 0.0], [-0.016473647, 0.12085977], [-0.016473647, -0.12085977]]} --> Real Eigen Values = [-0.70465113, 0.13846754, 0.13846754, -0.1614276, -0.1614276, -0.0068180511, -0.016473647, -0.016473647] real 0m10.984s user 0m9.319s sys 0m4.071s + status=0 + set +x ================================================= data/session06/7_avl_masstran_Eigen.py passed (as expected) ================================================= ================================================= 8_avl_friction_Link.py test; + python 8_avl_friction_Link.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) --> Mach = [0.1, 0.2, 0.30000000000000004, 0.4, 0.5, 0.6, 0.7000000000000001] --> CDp = [0.01592, 0.01416, 0.01323, 0.01259, 0.01209, 0.01167, 0.0113] --> CD = [0.02455060230115759, 0.02466896359668807, 0.02487666267824443, 0.02519203560974491, 0.02564765944813627, 0.02630249014988715, 0.02727263674182199] real 0m14.663s user 0m10.948s sys 0m5.046s + status=0 + set +x ================================================= data/session06/8_avl_friction_Link.py passed (as expected) ================================================= ================================================= avl_masstran_MainGear.py test; + python avl_masstran_MainGear.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Create masstran aim... ==> Computing mass properties... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wingSkin, index = 1 Name = fuseSkin, index = 2 Name = htailSkin, index = 3 Name = vtailSkin, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 5460 Number of elements = 10916 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 10916 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 4599 Number of elements = 9194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 9194 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2722 Number of elements = 5440 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 5440 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 18403 Combined Number of elements = 36790 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 36790 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuseSkin Property name - htailSkin Property name - vtailSkin Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input ==> Computed mass properties... --> aircraft_skin = {'mass': , 'CG': , 'massInertia': } ==> Creating AVL aim... ==> Outputs Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Writing mass properties file: caps.mass Parsing MassProp Note: The following floating-point exceptions are signalling: IEEE_DIVIDE_BY_ZERO --> Xcg = 89.1649 meter --> Xnp = 92.42451154634462 meter --> StaticMargin = 0.49270754323205207 --> EigenValues {'case 1': [[-0.70485396, 0.0], [0.13848718, 0.55142164], [0.13848718, -0.55142164], [-0.16432037, 0.56448129], [-0.16432037, -0.56448129], [-0.0068132786, 0.0], [-0.013683554, 0.11022262], [-0.013683554, -0.11022262]]} --> Real Eigen Values = [-0.70485396, 0.13848718, 0.13848718, -0.16432037, -0.16432037, -0.0068132786, -0.013683554, -0.013683554] real 0m10.079s user 0m8.577s sys 0m3.803s + status=0 + set +x ================================================= solutions/session06/avl_masstran_MainGear.py passed (as expected) ================================================= ================================================= avl_masstran_MultiMat.py test; + python avl_masstran_MultiMat.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Create masstran aim... ==> Computing mass properties... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wingSkin, index = 1 Name = fuseSkin, index = 2 Name = htailSkin, index = 3 Name = vtailSkin, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 5460 Number of elements = 10916 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 10916 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 4599 Number of elements = 9194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 9194 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2722 Number of elements = 5440 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 5440 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 18403 Combined Number of elements = 36790 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 36790 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 3 Material name - fuseium No "materialType" specified for Material tuple fuseium, defaulting to "Isotropic" Material name - tailium No "materialType" specified for Material tuple tailium, defaulting to "Isotropic" Material name - wingium No "materialType" specified for Material tuple wingium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuseSkin Property name - htailSkin Property name - vtailSkin Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input ==> Computed mass properties... --> aircraft_skin = {'mass': , 'CG': , 'massInertia': } ==> Creating AVL aim... ==> Outputs Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Writing mass properties file: caps.mass Parsing MassProp Note: The following floating-point exceptions are signalling: IEEE_DIVIDE_BY_ZERO --> Xcg = 80.225 meter --> Xnp = 92.49086830506504 meter --> StaticMargin = 1.8540509359079185 --> EigenValues {'case 1': [[-0.67265796, 0.0], [0.12206579, 0.57566948], [0.12206579, -0.57566948], [-0.15648068, 1.0547055], [-0.15648068, -1.0547055], [-0.0068086676, 0.0], [-0.0003299172, 0.049308002], [-0.0003299172, -0.049308002]]} --> Real Eigen Values = [-0.67265796, 0.12206579, 0.12206579, -0.15648068, -0.15648068, -0.0068086676, -0.0003299172, -0.0003299172] real 0m10.419s user 0m8.614s sys 0m4.168s + status=0 + set +x ================================================= solutions/session06/avl_masstran_MultiMat.py passed (as expected) ================================================= ================================================= masstran_MultiAIM.py test; + python masstran_MultiAIM.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Loading masstran aims... ==> Computing mass properties... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = fuseSkin, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 7445 Number of elements = 14886 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 14886 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - fuseium No "materialType" specified for Material tuple fuseium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - fuseSkin Done getting FEA properties Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wingSkin, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - wingium No "materialType" specified for Material tuple wingium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = htailSkin, index = 1 Name = vtailSkin, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 3488 Number of elements = 6972 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 6972 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 3480 Number of elements = 6956 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 6956 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 6968 Combined Number of elements = 13928 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 13928 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - tailium No "materialType" specified for Material tuple tailium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - htailSkin Property name - vtailSkin Done getting FEA properties Updating mesh element types based on properties input ==> Computed mass properties... --> fuse_skin = {'mass': , 'CG': , 'massInertia': } --> wing_skin = {'mass': , 'CG': , 'massInertia': } --> tail_skin = {'mass': , 'CG': , 'massInertia': } real 0m7.330s user 0m4.912s sys 0m3.139s + status=0 + set +x ================================================= solutions/session06/masstran_MultiAIM.py passed (as expected) ================================================= ================================================= masstran_MultiMat.py test; + python masstran_MultiMat.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Loading masstran aim... ==> Computing mass properties... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wingSkin, index = 1 Name = fuseSkin, index = 2 Name = htailSkin, index = 3 Name = vtailSkin, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 5460 Number of elements = 10916 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 10916 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 4599 Number of elements = 9194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 9194 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2722 Number of elements = 5440 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 5440 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 18403 Combined Number of elements = 36790 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 36790 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 3 Material name - fuseium No "materialType" specified for Material tuple fuseium, defaulting to "Isotropic" Material name - tailium No "materialType" specified for Material tuple tailium, defaulting to "Isotropic" Material name - wingium No "materialType" specified for Material tuple wingium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuseSkin Property name - htailSkin Property name - vtailSkin Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input ==> Computed mass properties... --> aircraft_skin = {'mass': , 'CG': , 'massInertia': } real 0m5.608s user 0m4.695s sys 0m1.651s + status=0 + set +x ================================================= solutions/session06/masstran_MultiMat.py passed (as expected) ================================================= ================================================= 01_aflr4_InviscidWing.py test; + python 01_aflr4_InviscidWing.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 6 EGADS : 2 Yes 0 0 1 0 1 1 4 5 EGADS : 3 Yes 0 0 1 0 1 1 4 8 EGADS : 4 Yes 0 0 1 0 1 2 3 5 EGADS : 5 Yes 0 0 1 0 1 2 4 EGADS : 6 Yes 0 0 1 0 1 1 7 8 EGADS : 7 Yes 0 0 1 0 1 6 9 10 EGADS : 8 Yes 0 0 1 0 1 3 6 9 EGADS : 9 Yes 0 0 1 0 1 7 8 10 EGADS : 10 Yes 0 0 1 0 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 428.342 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 8732 16959 0 AFLR4 : Nodes, Trias,Quads= 5233 9961 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 18090 35394 0 AFLR4 : Nodes, Trias,Quads= 5568 10350 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 10182 19859 0 AFLR4 : Nodes, Trias,Quads= 4951 9397 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 16338 31891 0 AFLR4 : Nodes, Trias,Quads= 5435 10085 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 55 71 0 AFLR4 : Nodes, Trias,Quads= 45 51 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 8705 16905 0 AFLR4 : Nodes, Trias,Quads= 5312 10119 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 17908 35030 0 AFLR4 : Nodes, Trias,Quads= 5567 10348 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 8823 17141 0 AFLR4 : Nodes, Trias,Quads= 4980 9455 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 16876 32967 0 AFLR4 : Nodes, Trias,Quads= 5357 9929 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 55 71 0 AFLR4 : Nodes, Trias,Quads= 46 53 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 112 186 0 AFLR4 : Nodes, Trias,Quads= 109 180 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 112 186 0 AFLR4 : Nodes, Trias,Quads= 109 180 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 113 188 0 AFLR4 : Nodes, Trias,Quads= 108 178 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 113 188 0 AFLR4 : Nodes, Trias,Quads= 109 180 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 113 188 0 AFLR4 : Nodes, Trias,Quads= 108 178 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 113 188 0 AFLR4 : Nodes, Trias,Quads= 109 180 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 40416 80824 5436 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 40416 80824 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 8498 16494 0 AFLR4 : Nodes, Trias,Quads= 6521 12540 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 14192 27608 0 AFLR4 : Nodes, Trias,Quads= 10030 19284 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 8900 17298 0 AFLR4 : Nodes, Trias,Quads= 6653 12804 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 13499 26224 0 AFLR4 : Nodes, Trias,Quads= 9809 18844 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 59 77 0 AFLR4 : Nodes, Trias,Quads= 49 57 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 8503 16504 0 AFLR4 : Nodes, Trias,Quads= 6543 12584 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 13624 26478 0 AFLR4 : Nodes, Trias,Quads= 9962 19154 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 8761 17020 0 AFLR4 : Nodes, Trias,Quads= 6664 12826 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 13534 26300 0 AFLR4 : Nodes, Trias,Quads= 9962 19156 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 60 79 0 AFLR4 : Nodes, Trias,Quads= 49 57 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 113 188 0 AFLR4 : Nodes, Trias,Quads= 109 180 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 111 184 0 AFLR4 : Nodes, Trias,Quads= 109 180 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 113 188 0 AFLR4 : Nodes, Trias,Quads= 107 176 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 113 188 0 AFLR4 : Nodes, Trias,Quads= 109 180 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 112 186 0 AFLR4 : Nodes, Trias,Quads= 108 178 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 112 186 0 AFLR4 : Nodes, Trias,Quads= 109 180 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 64194 128380 5374 OVERALL : CPU Time = 2.754 seconds Body 1 (of 2) Number of nodes = 63655 Number of elements = 127306 Number of triangle elements = 127306 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 539 Number of elements = 1074 Number of triangle elements = 1074 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 64194 Total number of elements = 128380 Total number of triangle elements = 128380 Total number of quadrilateral elements = 0 real 0m7.868s user 0m5.552s sys 0m2.082s + status=0 + set +x ================================================= data/session07/01_aflr4_InviscidWing.py passed (as expected) ================================================= ================================================= 02_aflr4_Farfield.py test; + python 02_aflr4_Farfield.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 6 EGADS : 2 Yes 0 0 1 0 1 1 4 5 EGADS : 3 Yes 0 0 1 0 1 1 4 8 EGADS : 4 Yes 0 0 1 0 1 2 3 5 EGADS : 5 Yes 0 0 1 0 1 2 4 EGADS : 6 Yes 0 0 1 0 1 1 7 8 EGADS : 7 Yes 0 0 1 0 1 6 9 10 EGADS : 8 Yes 0 0 1 0 1 3 6 9 EGADS : 9 Yes 0 0 1 0 1 7 8 10 EGADS : 10 Yes 0 0 1 0 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 530.302 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 8732 16959 0 AFLR4 : Nodes, Trias,Quads= 5233 9961 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 18090 35394 0 AFLR4 : Nodes, Trias,Quads= 5568 10350 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 10182 19859 0 AFLR4 : Nodes, Trias,Quads= 4951 9397 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 16338 31891 0 AFLR4 : Nodes, Trias,Quads= 5435 10085 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 55 71 0 AFLR4 : Nodes, Trias,Quads= 45 51 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 8705 16905 0 AFLR4 : Nodes, Trias,Quads= 5312 10119 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 17908 35030 0 AFLR4 : Nodes, Trias,Quads= 5567 10348 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 8823 17141 0 AFLR4 : Nodes, Trias,Quads= 4980 9455 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 16876 32967 0 AFLR4 : Nodes, Trias,Quads= 5357 9929 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 55 71 0 AFLR4 : Nodes, Trias,Quads= 46 53 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 40196 80384 5388 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 40196 80384 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 8498 16494 0 AFLR4 : Nodes, Trias,Quads= 6521 12540 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 14192 27608 0 AFLR4 : Nodes, Trias,Quads= 10030 19284 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 8900 17298 0 AFLR4 : Nodes, Trias,Quads= 6653 12804 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 13499 26224 0 AFLR4 : Nodes, Trias,Quads= 9809 18844 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 59 77 0 AFLR4 : Nodes, Trias,Quads= 49 57 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 8503 16504 0 AFLR4 : Nodes, Trias,Quads= 6543 12584 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 13624 26478 0 AFLR4 : Nodes, Trias,Quads= 9962 19154 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 8761 17020 0 AFLR4 : Nodes, Trias,Quads= 6664 12826 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 13534 26300 0 AFLR4 : Nodes, Trias,Quads= 9962 19156 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 60 79 0 AFLR4 : Nodes, Trias,Quads= 49 57 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 63975 127942 5326 OVERALL : CPU Time = 2.695 seconds Body 1 (of 2) Number of nodes = 63655 Number of elements = 127306 Number of triangle elements = 127306 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 320 Number of elements = 636 Number of triangle elements = 636 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 63975 Total number of elements = 127942 Total number of triangle elements = 127942 Total number of quadrilateral elements = 0 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 6 EGADS : 2 Yes 0 0 1 0 1 1 4 5 EGADS : 3 Yes 0 0 1 0 1 1 4 8 EGADS : 4 Yes 0 0 1 0 1 2 3 5 EGADS : 5 Yes 0 0 1 0 1 2 4 EGADS : 6 Yes 0 0 1 0 1 1 7 8 EGADS : 7 Yes 0 0 1 0 1 6 9 10 EGADS : 8 Yes 0 0 1 0 1 3 6 9 EGADS : 9 Yes 0 0 1 0 1 7 8 10 EGADS : 10 Yes 0 0 1 0 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 168.806 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 8732 16959 0 AFLR4 : Nodes, Trias,Quads= 5233 9961 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 18090 35394 0 AFLR4 : Nodes, Trias,Quads= 5568 10350 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 10182 19859 0 AFLR4 : Nodes, Trias,Quads= 4951 9397 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 16338 31891 0 AFLR4 : Nodes, Trias,Quads= 5435 10085 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 55 71 0 AFLR4 : Nodes, Trias,Quads= 45 51 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 8705 16905 0 AFLR4 : Nodes, Trias,Quads= 5312 10119 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 17908 35030 0 AFLR4 : Nodes, Trias,Quads= 5567 10348 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 8823 17141 0 AFLR4 : Nodes, Trias,Quads= 4980 9455 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 16876 32967 0 AFLR4 : Nodes, Trias,Quads= 5357 9929 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 55 71 0 AFLR4 : Nodes, Trias,Quads= 46 53 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 655 1216 0 AFLR4 : Nodes, Trias,Quads= 646 1198 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 655 1216 0 AFLR4 : Nodes, Trias,Quads= 644 1194 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 657 1220 0 AFLR4 : Nodes, Trias,Quads= 642 1190 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 653 1212 0 AFLR4 : Nodes, Trias,Quads= 644 1194 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 656 1218 0 AFLR4 : Nodes, Trias,Quads= 642 1190 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 654 1214 0 AFLR4 : Nodes, Trias,Quads= 645 1196 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 43459 86910 5772 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 43459 86910 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 8498 16494 0 AFLR4 : Nodes, Trias,Quads= 6521 12540 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 14192 27608 0 AFLR4 : Nodes, Trias,Quads= 10030 19284 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 8900 17298 0 AFLR4 : Nodes, Trias,Quads= 6653 12804 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 13499 26224 0 AFLR4 : Nodes, Trias,Quads= 9809 18844 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 59 77 0 AFLR4 : Nodes, Trias,Quads= 49 57 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 8503 16504 0 AFLR4 : Nodes, Trias,Quads= 6543 12584 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 13624 26478 0 AFLR4 : Nodes, Trias,Quads= 9962 19154 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 8761 17020 0 AFLR4 : Nodes, Trias,Quads= 6664 12826 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 13534 26300 0 AFLR4 : Nodes, Trias,Quads= 9962 19156 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 60 79 0 AFLR4 : Nodes, Trias,Quads= 49 57 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 671 1248 0 AFLR4 : Nodes, Trias,Quads= 642 1190 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 674 1254 0 AFLR4 : Nodes, Trias,Quads= 646 1198 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 670 1246 0 AFLR4 : Nodes, Trias,Quads= 645 1196 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 669 1244 0 AFLR4 : Nodes, Trias,Quads= 648 1202 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 672 1250 0 AFLR4 : Nodes, Trias,Quads= 643 1192 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 670 1246 0 AFLR4 : Nodes, Trias,Quads= 647 1200 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 67246 134484 5710 OVERALL : CPU Time = 2.775 seconds Body 1 (of 2) Number of nodes = 63655 Number of elements = 127306 Number of triangle elements = 127306 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 3591 Number of elements = 7178 Number of triangle elements = 7178 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 67246 Total number of elements = 134484 Total number of triangle elements = 134484 Total number of quadrilateral elements = 0 real 0m12.212s user 0m9.562s sys 0m2.220s + status=0 + set +x ================================================= data/session07/02_aflr4_Farfield.py passed (as expected) ================================================= ================================================= 03_aflr4_MeshLength.py test; + python 03_aflr4_MeshLength.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 6 EGADS : 2 Yes 0 0 1 0 1 1 4 5 EGADS : 3 Yes 0 0 1 0 1 1 4 8 EGADS : 4 Yes 0 0 1 0 1 2 3 5 EGADS : 5 Yes 0 0 1 0 1 2 4 EGADS : 6 Yes 0 0 1 0 1 1 7 8 EGADS : 7 Yes 0 0 1 0 1 6 9 10 EGADS : 8 Yes 0 0 1 0 1 3 6 9 EGADS : 9 Yes 0 0 1 0 1 7 8 10 EGADS : 10 Yes 0 0 1 0 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 530.379 AFLR4 : Abs Min Surf Spacing = 0.0217051 AFLR4 : Min Surf Spacing = 0.217051 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 3815 7343 0 AFLR4 : Nodes, Trias,Quads= 2646 5005 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 7205 13986 0 AFLR4 : Nodes, Trias,Quads= 2682 4940 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 3862 7438 0 AFLR4 : Nodes, Trias,Quads= 2506 4726 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 6786 13148 0 AFLR4 : Nodes, Trias,Quads= 2612 4800 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 39 50 0 AFLR4 : Nodes, Trias,Quads= 26 24 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 3812 7337 0 AFLR4 : Nodes, Trias,Quads= 2636 4985 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 7155 13886 0 AFLR4 : Nodes, Trias,Quads= 2677 4930 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 3757 7228 0 AFLR4 : Nodes, Trias,Quads= 2510 4734 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 6920 13416 0 AFLR4 : Nodes, Trias,Quads= 2582 4740 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 39 50 0 AFLR4 : Nodes, Trias,Quads= 26 24 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 19776 39544 3046 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 19776 39544 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 3762 7238 0 AFLR4 : Nodes, Trias,Quads= 3236 6186 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 6225 12029 0 AFLR4 : Nodes, Trias,Quads= 4493 8565 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 3744 7203 0 AFLR4 : Nodes, Trias,Quads= 3175 6065 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 5992 11563 0 AFLR4 : Nodes, Trias,Quads= 4332 8243 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 43 56 0 AFLR4 : Nodes, Trias,Quads= 29 28 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 3772 7258 0 AFLR4 : Nodes, Trias,Quads= 3224 6162 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 6189 11958 0 AFLR4 : Nodes, Trias,Quads= 4499 8578 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 3662 7039 0 AFLR4 : Nodes, Trias,Quads= 3196 6107 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 6229 12038 0 AFLR4 : Nodes, Trias,Quads= 4380 8340 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 43 56 0 AFLR4 : Nodes, Trias,Quads= 29 28 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 29473 58938 3032 OVERALL : CPU Time = 1.122 seconds Body 1 (of 2) Number of nodes = 29153 Number of elements = 58302 Number of triangle elements = 58302 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 320 Number of elements = 636 Number of triangle elements = 636 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 29473 Total number of elements = 58938 Total number of triangle elements = 58938 Total number of quadrilateral elements = 0 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 6 EGADS : 2 Yes 0 0 1 0 1 1 4 5 EGADS : 3 Yes 0 0 1 0 1 1 4 8 EGADS : 4 Yes 0 0 1 0 1 2 3 5 EGADS : 5 Yes 0 0 1 0 1 2 4 EGADS : 6 Yes 0 0 1 0 1 1 7 8 EGADS : 7 Yes 0 0 1 0 1 6 9 10 EGADS : 8 Yes 0 0 1 0 1 3 6 9 EGADS : 9 Yes 0 0 1 0 1 7 8 10 EGADS : 10 Yes 0 0 1 0 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 1591.14 AFLR4 : Abs Min Surf Spacing = 0.0217051 AFLR4 : Min Surf Spacing = 0.217051 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 3 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 890 1664 0 AFLR4 : Nodes, Trias,Quads= 575 1034 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1164 2167 0 AFLR4 : Nodes, Trias,Quads= 586 1011 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 884 1654 0 AFLR4 : Nodes, Trias,Quads= 539 964 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1120 2080 0 AFLR4 : Nodes, Trias,Quads= 569 978 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 17 20 0 AFLR4 : Nodes, Trias,Quads= 12 10 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 887 1658 0 AFLR4 : Nodes, Trias,Quads= 575 1034 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 1168 2175 0 AFLR4 : Nodes, Trias,Quads= 589 1017 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 880 1646 0 AFLR4 : Nodes, Trias,Quads= 535 956 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 1113 2066 0 AFLR4 : Nodes, Trias,Quads= 566 972 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 17 20 0 AFLR4 : Nodes, Trias,Quads= 12 10 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 4015 8022 1158 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 4015 8022 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 936 1754 0 AFLR4 : Nodes, Trias,Quads= 785 1452 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1193 2225 0 AFLR4 : Nodes, Trias,Quads= 985 1809 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 937 1757 0 AFLR4 : Nodes, Trias,Quads= 756 1395 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1171 2182 0 AFLR4 : Nodes, Trias,Quads= 949 1738 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 23 30 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 884 1650 0 AFLR4 : Nodes, Trias,Quads= 775 1432 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 1186 2212 0 AFLR4 : Nodes, Trias,Quads= 970 1780 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 884 1651 0 AFLR4 : Nodes, Trias,Quads= 765 1413 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 1164 2169 0 AFLR4 : Nodes, Trias,Quads= 949 1739 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 24 32 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 6413 12818 1170 OVERALL : CPU Time = 0.281 seconds Body 1 (of 2) Number of nodes = 6393 Number of elements = 12782 Number of triangle elements = 12782 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 20 Number of elements = 36 Number of triangle elements = 36 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 6413 Total number of elements = 12818 Total number of triangle elements = 12818 Total number of quadrilateral elements = 0 Getting mesh sizing parameters Mesh sizing name - Farfield Done getting mesh sizing parameters EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 6 EGADS : 2 Yes 0 0 1 0 1 1 4 5 EGADS : 3 Yes 0 0 1 0 1 1 4 8 EGADS : 4 Yes 0 0 1 0 1 2 3 5 EGADS : 5 Yes 0 0 1 0 1 2 4 EGADS : 6 Yes 0 0 1 0 1 1 7 8 EGADS : 7 Yes 0 0 1 0 1 6 9 10 EGADS : 8 Yes 0 0 1 0 1 3 6 9 EGADS : 9 Yes 0 0 1 0 1 7 8 10 EGADS : 10 Yes 0 0 1 0 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 4773.42 AFLR4 : Abs Min Surf Spacing = 0.0217051 AFLR4 : Min Surf Spacing = 0.217051 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 9 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 193 334 0 AFLR4 : Nodes, Trias,Quads= 166 280 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 259 452 0 AFLR4 : Nodes, Trias,Quads= 152 238 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 188 325 0 AFLR4 : Nodes, Trias,Quads= 150 249 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 245 424 0 AFLR4 : Nodes, Trias,Quads= 151 236 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 195 338 0 AFLR4 : Nodes, Trias,Quads= 166 280 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 258 450 0 AFLR4 : Nodes, Trias,Quads= 150 234 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 188 325 0 AFLR4 : Nodes, Trias,Quads= 151 251 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 244 422 0 AFLR4 : Nodes, Trias,Quads= 150 234 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 1013 2018 486 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 1013 2018 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 208 362 0 AFLR4 : Nodes, Trias,Quads= 203 352 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 242 420 0 AFLR4 : Nodes, Trias,Quads= 185 306 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 203 353 0 AFLR4 : Nodes, Trias,Quads= 190 327 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 243 422 0 AFLR4 : Nodes, Trias,Quads= 182 300 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 209 364 0 AFLR4 : Nodes, Trias,Quads= 200 346 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 246 427 0 AFLR4 : Nodes, Trias,Quads= 185 305 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 207 361 0 AFLR4 : Nodes, Trias,Quads= 195 337 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 248 431 0 AFLR4 : Nodes, Trias,Quads= 188 311 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 1316 2624 512 OVERALL : CPU Time = 0.159 seconds Body 1 (of 2) Number of nodes = 1296 Number of elements = 2588 Number of triangle elements = 2588 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 20 Number of elements = 36 Number of triangle elements = 36 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 1316 Total number of elements = 2624 Total number of triangle elements = 2624 Total number of quadrilateral elements = 0 real 0m5.860s user 0m3.681s sys 0m1.877s + status=0 + set +x ================================================= data/session07/03_aflr4_MeshLength.py passed (as expected) ================================================= ================================================= 04_aflr4_EdgeWeight.py test; + python 04_aflr4_EdgeWeight.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - leftWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 1 1 2 3 6 EGADS : 2 Yes 0 0 1 1 1 1 4 5 EGADS : 3 Yes 0 0 1 1 1 1 4 8 EGADS : 4 Yes 0 0 1 1 1 2 3 5 EGADS : 5 Yes 0 0 1 1 1 2 4 EGADS : 6 Yes 0 0 1 0 1 1 7 8 EGADS : 7 Yes 0 0 1 0 1 6 9 10 EGADS : 8 Yes 0 0 1 0 1 3 6 9 EGADS : 9 Yes 0 0 1 0 1 7 8 10 EGADS : 10 Yes 0 0 1 0 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 2651.51 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 5 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1107 2082 0 AFLR4 : Nodes, Trias,Quads= 685 1238 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1473 2759 0 AFLR4 : Nodes, Trias,Quads= 721 1255 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 1116 2100 0 AFLR4 : Nodes, Trias,Quads= 671 1210 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1458 2729 0 AFLR4 : Nodes, Trias,Quads= 714 1241 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 20 24 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1108 2084 0 AFLR4 : Nodes, Trias,Quads= 683 1234 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 1488 2789 0 AFLR4 : Nodes, Trias,Quads= 714 1241 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 1112 2092 0 AFLR4 : Nodes, Trias,Quads= 653 1174 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 1456 2725 0 AFLR4 : Nodes, Trias,Quads= 708 1229 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 20 24 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 4933 9858 1312 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 4933 9858 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 12796 24695 0 AFLR4 : Nodes, Trias,Quads= 7764 14631 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 29245 57075 0 AFLR4 : Nodes, Trias,Quads= 12448 23481 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 12136 23411 0 AFLR4 : Nodes, Trias,Quads= 7447 14033 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 29424 57435 0 AFLR4 : Nodes, Trias,Quads= 12399 23385 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 196 293 0 AFLR4 : Nodes, Trias,Quads= 188 277 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 2367 4490 0 AFLR4 : Nodes, Trias,Quads= 1726 3208 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 1453 2723 0 AFLR4 : Nodes, Trias,Quads= 1179 2175 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 1738 3267 0 AFLR4 : Nodes, Trias,Quads= 1397 2585 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 1477 2770 0 AFLR4 : Nodes, Trias,Quads= 1147 2110 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 26 35 0 AFLR4 : Nodes, Trias,Quads= 15 13 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 42971 85934 5550 OVERALL : CPU Time = 1.484 seconds Body 1 (of 2) Number of nodes = 42951 Number of elements = 85898 Number of triangle elements = 85898 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 20 Number of elements = 36 Number of triangle elements = 36 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 42971 Total number of elements = 85934 Total number of triangle elements = 85934 Total number of quadrilateral elements = 0 real 0m10.870s user 0m9.111s sys 0m1.763s + status=0 + set +x ================================================= data/session07/04_aflr4_EdgeWeight.py passed (as expected) ================================================= ================================================= 05_aflr4_ScaleFactor.py test; + python 05_aflr4_ScaleFactor.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - leftWing Mesh sizing name - riteWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 0.5 2 3 6 EGADS : 2 Yes 0 0 1 0 0.5 1 4 5 EGADS : 3 Yes 0 0 1 0 0.5 1 4 8 EGADS : 4 Yes 0 0 1 0 0.5 2 3 5 EGADS : 5 Yes 0 0 1 0 0.5 2 4 EGADS : 6 Yes 0 0 1 0 2 1 7 8 EGADS : 7 Yes 0 0 1 0 2 6 9 10 EGADS : 8 Yes 0 0 1 0 2 3 6 9 EGADS : 9 Yes 0 0 1 0 2 7 8 10 EGADS : 10 Yes 0 0 1 0 2 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 2651.51 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 5 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 2701 5174 0 AFLR4 : Nodes, Trias,Quads= 1493 2758 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 3760 7181 0 AFLR4 : Nodes, Trias,Quads= 1595 2851 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 2824 5420 0 AFLR4 : Nodes, Trias,Quads= 1415 2602 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 3766 7193 0 AFLR4 : Nodes, Trias,Quads= 1566 2793 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 32 40 0 AFLR4 : Nodes, Trias,Quads= 22 20 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 583 1067 0 AFLR4 : Nodes, Trias,Quads= 453 807 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 616 1125 0 AFLR4 : Nodes, Trias,Quads= 323 539 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 595 1091 0 AFLR4 : Nodes, Trias,Quads= 439 779 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 585 1063 0 AFLR4 : Nodes, Trias,Quads= 314 521 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 11 12 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 6848 13688 1584 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 6848 13688 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 2679 5130 0 AFLR4 : Nodes, Trias,Quads= 2106 3984 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 3433 6537 0 AFLR4 : Nodes, Trias,Quads= 2915 5501 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 2738 5248 0 AFLR4 : Nodes, Trias,Quads= 2089 3950 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 3483 6637 0 AFLR4 : Nodes, Trias,Quads= 2902 5475 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 34 44 0 AFLR4 : Nodes, Trias,Quads= 22 20 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 659 1212 0 AFLR4 : Nodes, Trias,Quads= 565 1024 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 636 1162 0 AFLR4 : Nodes, Trias,Quads= 481 852 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 640 1175 0 AFLR4 : Nodes, Trias,Quads= 542 979 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 608 1107 0 AFLR4 : Nodes, Trias,Quads= 462 815 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 11 12 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 11325 22642 1606 OVERALL : CPU Time = 0.444 seconds Body 1 (of 2) Number of nodes = 11305 Number of elements = 22606 Number of triangle elements = 22606 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 20 Number of elements = 36 Number of triangle elements = 36 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11325 Total number of elements = 22642 Total number of triangle elements = 22642 Total number of quadrilateral elements = 0 real 0m4.233s user 0m2.131s sys 0m1.960s + status=0 + set +x ================================================= data/session07/05_aflr4_ScaleFactor.py passed (as expected) ================================================= ================================================= 06_aflr4_Proximity.py test; + python 06_aflr4_Proximity.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml MESSAGE:: Building nacelleOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Nacelle, index = 1 Name = Wing, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Nacelle, index = 1 Name = leftWing, index = 2 Name = riteWing, index = 3 Name = Farfield, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - Nacelle Mesh sizing name - leftWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 4 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 4 Faces EGADS : Body 0 has 8 Edges EGADS : Body 0 has 4 Loops EGADS : Body 0 has 4 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 4 Faces EGADS : Body 1 has 8 Edges EGADS : Body 1 has 4 Loops EGADS : Body 1 has 4 Nodes EGADS : Body 2 is a SolidBody EGADS : Body 2 has 1 Shells EGADS : Body 2 has 10 Faces EGADS : Body 2 has 18 Edges EGADS : Body 2 has 10 Loops EGADS : Body 2 has 10 Nodes EGADS : Body 3 is a SolidBody EGADS : Body 3 has 1 Shells EGADS : Body 3 has 6 Faces EGADS : Body 3 has 12 Edges EGADS : Body 3 has 6 Loops EGADS : Body 3 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 0.5 2 3 EGADS : 2 Yes 0 0 1 0 0.5 1 4 EGADS : 3 Yes 0 0 1 0 0.5 1 4 EGADS : 4 Yes 0 0 1 0 0.5 2 3 EGADS : 5 Yes 1 0 1 0 0.5 6 7 EGADS : 6 Yes 1 0 1 0 0.5 5 8 EGADS : 7 Yes 1 0 1 0 0.5 5 8 EGADS : 8 Yes 1 0 1 0 0.5 6 7 EGADS : 9 Yes 2 0 1 0 50 10 11 14 EGADS : 10 Yes 2 0 1 0 50 9 12 13 EGADS : 11 Yes 2 0 1 0 50 9 12 16 EGADS : 12 Yes 2 0 1 0 50 10 11 13 EGADS : 13 Yes 2 0 1 0 50 10 12 EGADS : 14 Yes 2 0 1 0 1 9 15 16 EGADS : 15 Yes 2 0 1 0 1 14 17 18 EGADS : 16 Yes 2 0 1 0 1 11 14 17 EGADS : 17 Yes 2 0 1 0 1 15 16 18 EGADS : 18 Yes 2 0 1 0 1 15 17 EGADS : 19 Yes 3 0 1 NA NA 21 22 23 24 EGADS : 20 Yes 3 0 1 NA NA 21 22 23 24 EGADS : 21 Yes 3 0 1 NA NA 19 20 23 24 EGADS : 22 Yes 3 0 1 NA NA 19 20 23 24 EGADS : 23 Yes 3 0 1 NA NA 19 20 21 22 EGADS : 24 Yes 3 0 1 NA NA 19 20 21 22 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 3 2 -4 EGADS : 2 -2 5 1 -6 EGADS : 3 7 4 -8 -3 EGADS : 4 8 6 -7 -5 EGADS : 5 9 12 -10 -11 EGADS : 6 10 14 -9 -13 EGADS : 7 -15 11 16 -12 EGADS : 8 -16 13 15 -14 EGADS : 9 -17 18 19 -20 EGADS : 10 -21 20 22 -23 EGADS : 11 -19 24 17 -25 EGADS : 12 -22 25 21 -26 EGADS : 13 23 26 EGADS : 14 27 29 -28 -18 EGADS : 15 30 32 -31 -29 EGADS : 16 28 33 -27 -24 EGADS : 17 31 34 -30 -33 EGADS : 18 -32 -34 EGADS : 19 35 36 -37 -38 EGADS : 20 -39 42 41 -40 EGADS : 21 43 39 -44 -35 EGADS : 22 -45 37 46 -41 EGADS : 23 38 45 -42 -43 EGADS : 24 -36 44 40 -46 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : 17 17 EGADS : 18 18 EGADS : 19 19 EGADS : 20 20 EGADS : 21 21 EGADS : 22 22 EGADS : 23 23 EGADS : 24 24 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 3 2 -4 EGADS : 2 Yes -2 5 1 -6 EGADS : 3 Yes 7 4 -8 -3 EGADS : 4 Yes 8 6 -7 -5 EGADS : 5 Yes 9 12 -10 -11 EGADS : 6 Yes 10 14 -9 -13 EGADS : 7 Yes -15 11 16 -12 EGADS : 8 Yes -16 13 15 -14 EGADS : 9 Yes -17 18 19 -20 EGADS : 10 Yes -21 20 22 -23 EGADS : 11 Yes -19 24 17 -25 EGADS : 12 Yes -22 25 21 -26 EGADS : 13 Yes 23 26 EGADS : 14 Yes 27 29 -28 -18 EGADS : 15 Yes 30 32 -31 -29 EGADS : 16 Yes 28 33 -27 -24 EGADS : 17 Yes 31 34 -30 -33 EGADS : 18 Yes -32 -34 EGADS : 19 Yes 35 36 -37 -38 EGADS : 20 Yes -39 42 41 -40 EGADS : 21 Yes 43 39 -44 -35 EGADS : 22 Yes -45 37 46 -41 EGADS : 23 Yes 38 45 -42 -43 EGADS : 24 Yes -36 44 40 -46 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 2 EGADS : 2 0 Yes 3 4 1 1 2 EGADS : 3 0 Yes 1 3 1 1 3 EGADS : 4 0 Yes 2 4 1 1 3 EGADS : 5 0 Yes 3 1 1 2 4 EGADS : 6 0 Yes 4 2 1 2 4 EGADS : 7 0 Yes 1 2 1 3 4 EGADS : 8 0 Yes 3 4 1 3 4 EGADS : 9 1 Yes 5 6 1 5 6 EGADS : 10 1 Yes 7 8 1 5 6 EGADS : 11 1 Yes 5 7 1 5 7 EGADS : 12 1 Yes 6 8 1 5 7 EGADS : 13 1 Yes 7 5 1 6 8 EGADS : 14 1 Yes 8 6 1 6 8 EGADS : 15 1 Yes 5 6 1 7 8 EGADS : 16 1 Yes 7 8 1 7 8 EGADS : 17 2 Yes 9 10 1 9 11 EGADS : 18 2 Yes 9 11 1 9 14 EGADS : 19 2 Yes 11 12 1 9 11 EGADS : 20 2 Yes 10 12 1 9 10 EGADS : 21 2 Yes 10 13 1 10 12 EGADS : 22 2 Yes 12 14 1 10 12 EGADS : 23 2 Yes 13 14 1 10 13 EGADS : 24 2 Yes 11 9 1 11 16 EGADS : 25 2 Yes 12 10 1 11 12 EGADS : 26 2 Yes 14 13 1 12 13 EGADS : 27 2 Yes 9 15 1 14 16 EGADS : 28 2 Yes 11 16 1 14 16 EGADS : 29 2 Yes 15 16 1 14 15 EGADS : 30 2 Yes 15 17 1 15 17 EGADS : 31 2 Yes 16 18 1 15 17 EGADS : 32 2 Yes 17 18 1 15 18 EGADS : 33 2 Yes 16 15 1 16 17 EGADS : 34 2 Yes 18 17 1 17 18 EGADS : 35 3 Yes 20 19 NA 19 21 EGADS : 36 3 Yes 19 21 NA 19 24 EGADS : 37 3 Yes 22 21 NA 19 22 EGADS : 38 3 Yes 20 22 NA 19 23 EGADS : 39 3 Yes 24 23 NA 20 21 EGADS : 40 3 Yes 23 25 NA 20 24 EGADS : 41 3 Yes 26 25 NA 20 22 EGADS : 42 3 Yes 24 26 NA 20 23 EGADS : 43 3 Yes 20 24 NA 21 23 EGADS : 44 3 Yes 19 23 NA 21 24 EGADS : 45 3 Yes 22 26 NA 22 23 EGADS : 46 3 Yes 21 25 NA 22 24 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 90.5173952 0 0 EGADS : 2 Yes 90.5173952 0 0 EGADS : 3 Yes 60.5173952 0 0 EGADS : 4 Yes 60.5173952 0 0 EGADS : 5 Yes 90.5173952 29.3018771 0 EGADS : 6 Yes 90.5173952 29.3018771 0 EGADS : 7 Yes 60.5173952 29.3018771 0 EGADS : 8 Yes 60.5173952 29.3018771 0 EGADS : 9 Yes 97.2007855 0 0 EGADS : 10 Yes 97.9335611 0 0 EGADS : 11 Yes 50 0 0 EGADS : 12 Yes 75.3047874 0 0 EGADS : 13 Yes 123.552357 0 4.7180639 EGADS : 14 Yes 118.391317 0 3.99272703 EGADS : 15 Yes 97.9335611 36.1389817 0 EGADS : 16 Yes 75.3047874 36.1389817 0 EGADS : 17 Yes 123.552357 97.6729236 4.7180639 EGADS : 18 Yes 118.391317 97.6729236 3.99272703 EGADS : 19 Yes 0 0 1947.05079 EGADS : 20 Yes 0 0 0 EGADS : 21 Yes 0 1953.45847 1947.05079 EGADS : 22 Yes 0 1953.45847 0 EGADS : 23 Yes 2040.21562 0 1947.05079 EGADS : 24 Yes 2040.21562 0 0 EGADS : 25 Yes 2040.21562 1953.45847 1947.05079 EGADS : 26 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 22.2515 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 530.302 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 STD w/BL AFLR4 : 12 CAD geometry 0 STD w/BL AFLR4 : 13 CAD geometry 0 STD w/BL AFLR4 : 14 CAD geometry 0 STD w/BL AFLR4 : 15 CAD geometry 0 STD w/BL AFLR4 : 16 CAD geometry 0 STD w/BL AFLR4 : 17 CAD geometry 0 STD w/BL AFLR4 : 18 CAD geometry 0 STD w/BL AFLR4 : 19 CAD geometry 0 FARFIELD AFLR4 : 20 CAD geometry 0 FARFIELD AFLR4 : 21 CAD geometry 0 FARFIELD AFLR4 : 22 CAD geometry 0 FARFIELD AFLR4 : 23 CAD geometry 0 FARFIELD AFLR4 : 24 CAD geometry 0 FARFIELD AFLR4 : Case has 2 Proximity Checking Components AFLR4 : Component 1 includes Definitions 9 10 11 12 13 14 15 16 17 18 AFLR4 : Component 2 includes Definitions 1 2 3 4 5 6 7 8 AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Define CAD surface definition 17 AFLR4 : Define CAD surface definition 18 AFLR4 : Define CAD surface definition 19 AFLR4 : Define CAD surface definition 20 AFLR4 : Define CAD surface definition 21 AFLR4 : Define CAD surface definition 22 AFLR4 : Define CAD surface definition 23 AFLR4 : Define CAD surface definition 24 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 13740 26927 0 AFLR4 : Nodes, Trias,Quads= 13723 26893 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 18558 36477 0 AFLR4 : Nodes, Trias,Quads= 16589 32539 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 13776 26999 0 AFLR4 : Nodes, Trias,Quads= 13736 26919 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 18524 36409 0 AFLR4 : Nodes, Trias,Quads= 16538 32437 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 13776 26999 0 AFLR4 : Nodes, Trias,Quads= 13736 26919 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 18524 36409 0 AFLR4 : Nodes, Trias,Quads= 16538 32437 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 13740 26927 0 AFLR4 : Nodes, Trias,Quads= 13723 26893 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 18558 36477 0 AFLR4 : Nodes, Trias,Quads= 16589 32539 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 502 907 0 AFLR4 : Nodes, Trias,Quads= 423 749 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 85 133 0 AFLR4 : Nodes, Trias,Quads= 56 75 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 502 907 0 AFLR4 : Nodes, Trias,Quads= 399 701 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 84 131 0 AFLR4 : Nodes, Trias,Quads= 55 73 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 8705 16905 0 AFLR4 : Nodes, Trias,Quads= 5312 10119 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 17908 35030 0 AFLR4 : Nodes, Trias,Quads= 5567 10348 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 8823 17141 0 AFLR4 : Nodes, Trias,Quads= 4980 9455 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 16876 32967 0 AFLR4 : Nodes, Trias,Quads= 5357 9929 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 55 71 0 AFLR4 : Nodes, Trias,Quads= 46 53 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 139862 279716 7794 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 139862 279716 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 13776 26996 0 AFLR4 : Nodes, Trias,Quads= 13887 27218 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 18675 36709 0 AFLR4 : Nodes, Trias,Quads= 16689 32737 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 13883 27210 0 AFLR4 : Nodes, Trias,Quads= 13963 27370 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 18667 36693 0 AFLR4 : Nodes, Trias,Quads= 16618 32595 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 13883 27210 0 AFLR4 : Nodes, Trias,Quads= 13963 27370 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 18667 36693 0 AFLR4 : Nodes, Trias,Quads= 16618 32595 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 13776 26996 0 AFLR4 : Nodes, Trias,Quads= 13887 27218 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 18675 36709 0 AFLR4 : Nodes, Trias,Quads= 16689 32737 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 525 950 0 AFLR4 : Nodes, Trias,Quads= 470 840 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 91 144 0 AFLR4 : Nodes, Trias,Quads= 59 80 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 538 976 0 AFLR4 : Nodes, Trias,Quads= 443 786 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 90 142 0 AFLR4 : Nodes, Trias,Quads= 58 78 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 8695 16888 0 AFLR4 : Nodes, Trias,Quads= 6539 12576 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 13624 26478 0 AFLR4 : Nodes, Trias,Quads= 9962 19154 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 8700 16899 0 AFLR4 : Nodes, Trias,Quads= 6656 12811 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 13534 26300 0 AFLR4 : Nodes, Trias,Quads= 9962 19156 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 60 79 0 AFLR4 : Nodes, Trias,Quads= 49 57 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 153012 306016 7784 AFLR4 : Proximity BG Surface Grid Generation AFLR4 : Nodes, Trias = 153400 306792 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 13935 27308 0 AFLR4 : Nodes, Trias,Quads= 13791 27020 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 18710 36774 0 AFLR4 : Nodes, Trias,Quads= 16564 32482 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 13945 27328 0 AFLR4 : Nodes, Trias,Quads= 13842 27122 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 18677 36708 0 AFLR4 : Nodes, Trias,Quads= 16540 32434 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 13945 27328 0 AFLR4 : Nodes, Trias,Quads= 13842 27122 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 18677 36708 0 AFLR4 : Nodes, Trias,Quads= 16540 32434 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 13935 27308 0 AFLR4 : Nodes, Trias,Quads= 13791 27020 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 18710 36774 0 AFLR4 : Nodes, Trias,Quads= 16564 32482 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 699 1265 0 AFLR4 : Nodes, Trias,Quads= 814 1495 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 103 166 0 AFLR4 : Nodes, Trias,Quads= 63 86 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 1128 2110 0 AFLR4 : Nodes, Trias,Quads= 1749 3352 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 146 239 0 AFLR4 : Nodes, Trias,Quads= 186 319 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 8764 17019 0 AFLR4 : Nodes, Trias,Quads= 7128 13747 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 15673 30550 0 AFLR4 : Nodes, Trias,Quads= 11025 21254 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 9004 17499 0 AFLR4 : Nodes, Trias,Quads= 7783 15057 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 15491 30186 0 AFLR4 : Nodes, Trias,Quads= 11025 21254 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 61 80 0 AFLR4 : Nodes, Trias,Quads= 50 58 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 157692 315376 7994 OVERALL : CPU Time = 12.245 seconds Body 1 (of 4) Number of nodes = 59529 Number of elements = 119058 Number of triangle elements = 119058 Number of quadrilateral elements = 0 Body 2 (of 4) Number of nodes = 59529 Number of elements = 119058 Number of triangle elements = 119058 Number of quadrilateral elements = 0 Body 3 (of 4) Number of nodes = 38314 Number of elements = 76624 Number of triangle elements = 76624 Number of quadrilateral elements = 0 Body 4 (of 4) Number of nodes = 320 Number of elements = 636 Number of triangle elements = 636 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 157692 Total number of elements = 315376 Total number of triangle elements = 315376 Total number of quadrilateral elements = 0 real 0m22.018s user 0m19.025s sys 0m2.569s + status=0 + set +x ================================================= data/session07/06_aflr4_Proximity.py passed (as expected) ================================================= ================================================= 07_aflr4_ProximityComponents.py test; + python 07_aflr4_ProximityComponents.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml MESSAGE:: Building pylonOml MESSAGE:: Building nacelleOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing, index = 1 Name = Pylon, index = 2 Name = Nacelle, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Pylon, index = 3 Name = Nacelle, index = 4 Name = Farfield, index = 5 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - Nacelle Mesh sizing name - Pylon Mesh sizing name - leftWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 22 Faces EGADS : Body 0 has 48 Edges EGADS : Body 0 has 24 Loops EGADS : Body 0 has 26 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 50 2 3 4 EGADS : 2 Yes 0 0 1 0 50 1 5 6 7 8 EGADS : 3 Yes 0 0 1 0 1 1 5 9 EGADS : 4 Yes 0 0 1 0 50 1 6 10 EGADS : 5 Yes 0 0 1 0 1 2 3 11 12 13 EGADS : 6 Yes 0 0 1 0 50 2 4 10 EGADS : 7 Yes 0 0 1 0 10 2 8 14 EGADS : 8 Yes 0 0 1 0 10 2 7 15 EGADS : 9 Yes 0 0 1 0 1 3 11 16 EGADS : 10 Yes 0 0 1 0 50 4 6 EGADS : 11 Yes 0 0 1 0 1 5 9 16 EGADS : 12 Yes 0 0 1 0 10 5 13 17 EGADS : 13 Yes 0 0 1 0 10 5 12 18 EGADS : 14 Yes 0 0 1 0 0.5 7 15 19 EGADS : 15 Yes 0 0 1 0 0.5 8 14 20 EGADS : 16 Yes 0 0 1 0 1 9 11 EGADS : 17 Yes 0 0 1 0 0.5 12 18 21 EGADS : 18 Yes 0 0 1 0 0.5 13 17 22 EGADS : 19 Yes 0 0 1 0 0.5 14 20 EGADS : 20 Yes 0 0 1 0 0.5 15 19 EGADS : 21 Yes 0 0 1 0 0.5 17 22 EGADS : 22 Yes 0 0 1 0 0.5 18 21 EGADS : 23 Yes 1 0 1 NA NA 25 26 27 28 EGADS : 24 Yes 1 0 1 NA NA 25 26 27 28 EGADS : 25 Yes 1 0 1 NA NA 23 24 27 28 EGADS : 26 Yes 1 0 1 NA NA 23 24 27 28 EGADS : 27 Yes 1 0 1 NA NA 23 24 25 26 EGADS : 28 Yes 1 0 1 NA NA 23 24 25 26 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -3 5 1 -6 7 8 EGADS : 3 9 11 -10 -2 EGADS : 4 -12 4 13 -14 EGADS : 5 10 15 -9 -5 16 17 EGADS : 6 -13 6 12 -18 EGADS : 7 19 20 -7 -21 EGADS : 8 21 -8 -20 -22 EGADS : 9 23 25 -24 -11 EGADS : 10 14 18 EGADS : 11 24 26 -23 -15 EGADS : 12 -27 29 -16 -28 EGADS : 13 -29 30 28 -17 EGADS : 14 31 -19 32 33 -34 -35 EGADS : 15 -31 37 34 -36 -32 22 EGADS : 16 -25 -26 EGADS : 17 38 27 39 40 -41 -42 EGADS : 18 -38 44 41 -43 -39 -30 EGADS : 19 -33 45 35 -46 EGADS : 20 36 46 -37 -45 EGADS : 21 -40 47 42 -48 EGADS : 22 43 48 -44 -47 EGADS : 23 49 50 -51 -52 EGADS : 24 -53 56 55 -54 EGADS : 25 57 53 -58 -49 EGADS : 26 -59 51 60 -55 EGADS : 27 52 59 -56 -57 EGADS : 28 -50 58 54 -60 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 3 EGADS : 3 4 EGADS : 4 5 EGADS : 5 6 7 EGADS : 6 8 EGADS : 7 9 EGADS : 8 10 EGADS : 9 11 EGADS : 10 12 EGADS : 11 13 EGADS : 12 14 EGADS : 13 15 EGADS : 14 16 EGADS : 15 17 EGADS : 16 18 EGADS : 17 19 EGADS : 18 20 EGADS : 19 21 EGADS : 20 22 EGADS : 21 23 EGADS : 22 24 EGADS : 23 25 EGADS : 24 26 EGADS : 25 27 EGADS : 26 28 EGADS : 27 29 EGADS : 28 30 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -3 5 1 -6 EGADS : 3 Yes 7 8 EGADS : 4 Yes 9 11 -10 -2 EGADS : 5 Yes -12 4 13 -14 EGADS : 6 Yes 10 15 -9 -5 EGADS : 7 Yes 16 17 EGADS : 8 Yes -13 6 12 -18 EGADS : 9 Yes 19 20 -7 -21 EGADS : 10 Yes 21 -8 -20 -22 EGADS : 11 Yes 23 25 -24 -11 EGADS : 12 Yes 14 18 EGADS : 13 Yes 24 26 -23 -15 EGADS : 14 Yes -27 29 -16 -28 EGADS : 15 Yes -29 30 28 -17 EGADS : 16 Yes 31 -19 32 33 -34 -35 EGADS : 17 Yes -31 37 34 -36 -32 22 EGADS : 18 Yes -25 -26 EGADS : 19 Yes 38 27 39 40 -41 -42 EGADS : 20 Yes -38 44 41 -43 -39 -30 EGADS : 21 Yes -33 45 35 -46 EGADS : 22 Yes 36 46 -37 -45 EGADS : 23 Yes -40 47 42 -48 EGADS : 24 Yes 43 48 -44 -47 EGADS : 25 Yes 49 50 -51 -52 EGADS : 26 Yes -53 56 55 -54 EGADS : 27 Yes 57 53 -58 -49 EGADS : 28 Yes -59 51 60 -55 EGADS : 29 Yes 52 59 -56 -57 EGADS : 30 Yes -50 58 54 -60 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 2 EGADS : 2 0 Yes 1 3 1 1 3 EGADS : 3 0 Yes 3 4 1 1 2 EGADS : 4 0 Yes 2 4 1 1 4 EGADS : 5 0 Yes 3 1 1 2 5 EGADS : 6 0 Yes 4 2 1 2 6 EGADS : 7 0 Yes 5 6 1 2 7 EGADS : 8 0 Yes 6 5 1 2 8 EGADS : 9 0 Yes 1 7 1 3 5 EGADS : 10 0 Yes 3 8 1 3 5 EGADS : 11 0 Yes 7 8 1 3 9 EGADS : 12 0 Yes 2 9 1 4 6 EGADS : 13 0 Yes 4 10 1 4 6 EGADS : 14 0 Yes 9 10 1 4 10 EGADS : 15 0 Yes 8 7 1 5 11 EGADS : 16 0 Yes 11 12 1 5 12 EGADS : 17 0 Yes 12 11 1 5 13 EGADS : 18 0 Yes 10 9 1 6 10 EGADS : 19 0 Yes 13 14 1 7 14 EGADS : 20 0 Yes 14 6 1 7 8 EGADS : 21 0 Yes 13 5 1 7 8 EGADS : 22 0 Yes 13 14 1 8 15 EGADS : 23 0 Yes 7 15 1 9 11 EGADS : 24 0 Yes 8 16 1 9 11 EGADS : 25 0 Yes 15 16 1 9 16 EGADS : 26 0 Yes 16 15 1 11 16 EGADS : 27 0 Yes 17 18 1 12 17 EGADS : 28 0 Yes 18 11 1 12 13 EGADS : 29 0 Yes 17 12 1 12 13 EGADS : 30 0 Yes 17 18 1 13 18 EGADS : 31 0 Yes 19 14 1 14 15 EGADS : 32 0 Yes 13 20 1 14 15 EGADS : 33 0 Yes 20 21 1 14 19 EGADS : 34 0 Yes 22 21 1 14 15 EGADS : 35 0 Yes 19 22 1 14 19 EGADS : 36 0 Yes 20 21 1 15 20 EGADS : 37 0 Yes 19 22 1 15 20 EGADS : 38 0 Yes 23 17 1 17 18 EGADS : 39 0 Yes 18 24 1 17 18 EGADS : 40 0 Yes 24 25 1 17 21 EGADS : 41 0 Yes 26 25 1 17 18 EGADS : 42 0 Yes 23 26 1 17 21 EGADS : 43 0 Yes 24 25 1 18 22 EGADS : 44 0 Yes 23 26 1 18 22 EGADS : 45 0 Yes 20 19 1 19 20 EGADS : 46 0 Yes 21 22 1 19 20 EGADS : 47 0 Yes 24 23 1 21 22 EGADS : 48 0 Yes 25 26 1 21 22 EGADS : 49 1 Yes 28 27 NA 23 25 EGADS : 50 1 Yes 27 29 NA 23 28 EGADS : 51 1 Yes 30 29 NA 23 26 EGADS : 52 1 Yes 28 30 NA 23 27 EGADS : 53 1 Yes 32 31 NA 24 25 EGADS : 54 1 Yes 31 33 NA 24 28 EGADS : 55 1 Yes 34 33 NA 24 26 EGADS : 56 1 Yes 32 34 NA 24 27 EGADS : 57 1 Yes 28 32 NA 25 27 EGADS : 58 1 Yes 27 31 NA 25 28 EGADS : 59 1 Yes 30 34 NA 26 27 EGADS : 60 1 Yes 29 33 NA 26 28 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 72.4759225 0 0 EGADS : 6 Yes 83.5054156 0 0 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 0 4.7180639 EGADS : 10 Yes 118.391317 0 3.99272703 EGADS : 11 Yes 72.4759225 29.3018771 0 EGADS : 12 Yes 83.5054156 29.3018771 0 EGADS : 13 Yes 70.524066 0 0 EGADS : 14 Yes 79.4370049 0 0 EGADS : 15 Yes 123.552357 97.6729236 4.7180639 EGADS : 16 Yes 118.391317 97.6729236 3.99272703 EGADS : 17 Yes 79.4370049 29.3018771 0 EGADS : 18 Yes 70.524066 29.3018771 0 EGADS : 19 Yes 90.5173952 0 0 EGADS : 20 Yes 60.5173952 0 0 EGADS : 21 Yes 60.5173952 0 0 EGADS : 22 Yes 90.5173952 0 0 EGADS : 23 Yes 90.5173952 29.3018771 0 EGADS : 24 Yes 60.5173952 29.3018771 0 EGADS : 25 Yes 60.5173952 29.3018771 0 EGADS : 26 Yes 90.5173952 29.3018771 0 EGADS : 27 Yes 0 0 1947.05079 EGADS : 28 Yes 0 0 0 EGADS : 29 Yes 0 1953.45847 1947.05079 EGADS : 30 Yes 0 1953.45847 0 EGADS : 31 Yes 2040.21562 0 1947.05079 EGADS : 32 Yes 2040.21562 0 0 EGADS : 33 Yes 2040.21562 1953.45847 1947.05079 EGADS : 34 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 22.2515 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 530.302 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 STD w/BL AFLR4 : 12 CAD geometry 0 STD w/BL AFLR4 : 13 CAD geometry 0 STD w/BL AFLR4 : 14 CAD geometry 0 STD w/BL AFLR4 : 15 CAD geometry 0 STD w/BL AFLR4 : 16 CAD geometry 0 STD w/BL AFLR4 : 17 CAD geometry 0 STD w/BL AFLR4 : 18 CAD geometry 0 STD w/BL AFLR4 : 19 CAD geometry 0 STD w/BL AFLR4 : 20 CAD geometry 0 STD w/BL AFLR4 : 21 CAD geometry 0 STD w/BL AFLR4 : 22 CAD geometry 0 STD w/BL AFLR4 : 23 CAD geometry 0 FARFIELD AFLR4 : 24 CAD geometry 0 FARFIELD AFLR4 : 25 CAD geometry 0 FARFIELD AFLR4 : 26 CAD geometry 0 FARFIELD AFLR4 : 27 CAD geometry 0 FARFIELD AFLR4 : 28 CAD geometry 0 FARFIELD AFLR4 : Case has 3 Proximity Checking Components AFLR4 : Component 1 includes Definitions 1 2 3 4 5 6 9 10 11 16 AFLR4 : Component 2 includes Definitions 14 15 17 18 19 20 21 22 AFLR4 : Component 3 includes Definitions 7 8 12 13 AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Define CAD surface definition 17 AFLR4 : Define CAD surface definition 18 AFLR4 : Define CAD surface definition 19 AFLR4 : Define CAD surface definition 20 AFLR4 : Define CAD surface definition 21 AFLR4 : Define CAD surface definition 22 AFLR4 : Define CAD surface definition 23 AFLR4 : Define CAD surface definition 24 AFLR4 : Define CAD surface definition 25 AFLR4 : Define CAD surface definition 26 AFLR4 : Define CAD surface definition 27 AFLR4 : Define CAD surface definition 28 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 502 907 0 AFLR4 : Nodes, Trias,Quads= 423 749 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 769 1416 0 AFLR4 : Nodes, Trias,Quads= 579 1036 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 8705 16905 0 AFLR4 : Nodes, Trias,Quads= 5312 10119 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 85 133 0 AFLR4 : Nodes, Trias,Quads= 56 75 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 9412 18267 0 AFLR4 : Nodes, Trias,Quads= 5160 9763 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 84 131 0 AFLR4 : Nodes, Trias,Quads= 55 73 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 382 673 0 AFLR4 : Nodes, Trias,Quads= 221 351 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 377 662 0 AFLR4 : Nodes, Trias,Quads= 227 362 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 17908 35030 0 AFLR4 : Nodes, Trias,Quads= 5567 10348 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 16876 32967 0 AFLR4 : Nodes, Trias,Quads= 5357 9929 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 536 964 0 AFLR4 : Nodes, Trias,Quads= 324 540 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 530 952 0 AFLR4 : Nodes, Trias,Quads= 325 542 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 14942 29305 0 AFLR4 : Nodes, Trias,Quads= 14513 28447 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 14940 29301 0 AFLR4 : Nodes, Trias,Quads= 14427 28275 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 55 71 0 AFLR4 : Nodes, Trias,Quads= 46 53 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 14942 29305 0 AFLR4 : Nodes, Trias,Quads= 14513 28447 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 14928 29277 0 AFLR4 : Nodes, Trias,Quads= 14400 28221 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 18558 36477 0 AFLR4 : Nodes, Trias,Quads= 16589 32539 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 18524 36409 0 AFLR4 : Nodes, Trias,Quads= 16538 32437 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 18558 36477 0 AFLR4 : Nodes, Trias,Quads= 16589 32539 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 18524 36409 0 AFLR4 : Nodes, Trias,Quads= 16538 32437 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 25 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 26 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 27 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 28 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 143960 287920 8370 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 143960 287920 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 552 1002 0 AFLR4 : Nodes, Trias,Quads= 474 846 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 803 1479 0 AFLR4 : Nodes, Trias,Quads= 727 1327 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 8664 16826 0 AFLR4 : Nodes, Trias,Quads= 6539 12576 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 94 149 0 AFLR4 : Nodes, Trias,Quads= 60 81 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 9289 18022 0 AFLR4 : Nodes, Trias,Quads= 6959 13362 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 92 145 0 AFLR4 : Nodes, Trias,Quads= 59 79 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 375 660 0 AFLR4 : Nodes, Trias,Quads= 275 460 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 386 681 0 AFLR4 : Nodes, Trias,Quads= 270 449 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 13624 26478 0 AFLR4 : Nodes, Trias,Quads= 9962 19154 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 13541 26314 0 AFLR4 : Nodes, Trias,Quads= 9962 19156 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 573 1036 0 AFLR4 : Nodes, Trias,Quads= 363 616 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 580 1049 0 AFLR4 : Nodes, Trias,Quads= 370 629 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 15123 29666 0 AFLR4 : Nodes, Trias,Quads= 14638 28696 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 15402 30224 0 AFLR4 : Nodes, Trias,Quads= 14606 28632 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 60 79 0 AFLR4 : Nodes, Trias,Quads= 49 57 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 15284 29986 0 AFLR4 : Nodes, Trias,Quads= 14698 28814 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 15598 30614 0 AFLR4 : Nodes, Trias,Quads= 14616 28650 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 18664 36687 0 AFLR4 : Nodes, Trias,Quads= 16684 32727 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 18711 36781 0 AFLR4 : Nodes, Trias,Quads= 16625 32609 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 18664 36687 0 AFLR4 : Nodes, Trias,Quads= 16684 32727 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 18712 36783 0 AFLR4 : Nodes, Trias,Quads= 16612 32583 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 25 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 26 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 27 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 28 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 157434 314868 8368 AFLR4 : Proximity BG Surface Grid Generation AFLR4 : Nodes, Trias = 159274 318548 AFLR4 : Nodes, Trias = 159694 319388 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1086 2020 0 AFLR4 : Nodes, Trias,Quads= 962 1772 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 2773 5270 0 AFLR4 : Nodes, Trias,Quads= 2797 5318 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 8783 17057 0 AFLR4 : Nodes, Trias,Quads= 7137 13765 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 184 310 0 AFLR4 : Nodes, Trias,Quads= 138 218 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 16222 31763 0 AFLR4 : Nodes, Trias,Quads= 9485 18289 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 232 397 0 AFLR4 : Nodes, Trias,Quads= 221 375 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 1413 2643 0 AFLR4 : Nodes, Trias,Quads= 911 1639 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 1587 2978 0 AFLR4 : Nodes, Trias,Quads= 1002 1808 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 15687 30578 0 AFLR4 : Nodes, Trias,Quads= 11055 21314 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 15518 30240 0 AFLR4 : Nodes, Trias,Quads= 11034 21272 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 2345 4452 0 AFLR4 : Nodes, Trias,Quads= 1526 2814 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 2241 4252 0 AFLR4 : Nodes, Trias,Quads= 1462 2694 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 17583 34542 0 AFLR4 : Nodes, Trias,Quads= 14783 28942 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 17575 34524 0 AFLR4 : Nodes, Trias,Quads= 14759 28892 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 61 80 0 AFLR4 : Nodes, Trias,Quads= 50 58 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 19924 39212 0 AFLR4 : Nodes, Trias,Quads= 14954 29272 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 18844 37054 0 AFLR4 : Nodes, Trias,Quads= 14853 29072 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 18691 36736 0 AFLR4 : Nodes, Trias,Quads= 16527 32408 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 18718 36790 0 AFLR4 : Nodes, Trias,Quads= 16525 32404 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 18691 36736 0 AFLR4 : Nodes, Trias,Quads= 16527 32408 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 18709 36772 0 AFLR4 : Nodes, Trias,Quads= 16535 32424 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 25 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 26 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 27 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 28 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 168898 337796 9462 OVERALL : CPU Time = 14.698 seconds Body 1 (of 2) Number of nodes = 168578 Number of elements = 337160 Number of triangle elements = 337160 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 320 Number of elements = 636 Number of triangle elements = 636 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 168898 Total number of elements = 337796 Total number of triangle elements = 337796 Total number of quadrilateral elements = 0 real 0m30.437s user 0m30.473s sys 0m3.430s + status=0 + set +x ================================================= data/session07/07_aflr4_ProximityComponents.py passed (as expected) ================================================= ================================================= 08_aflr4_InviscidTransport.py test; + python 08_aflr4_InviscidTransport.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml MESSAGE:: Building wingHinges MESSAGE:: Building nacelleOml MESSAGE:: Building htailOml MESSAGE:: Building htailHinges MESSAGE:: Building vtailOml MESSAGE:: Building vtailHinges MESSAGE:: Building fuseOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = Nacelle, index = 1 Name = Vtail, index = 2 Name = Htail, index = 3 Name = Fuselage, index = 4 Name = Wing, index = 5 Name = Farfield, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 7 Name = Nacelle, index = 1 Name = Vtail, index = 2 Name = Htail, index = 3 Name = Fuselage, index = 4 Name = riteWing, index = 5 Name = leftWing, index = 6 Name = Farfield, index = 7 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - Htail Mesh sizing name - Nacelle Mesh sizing name - Vtail Mesh sizing name - leftWing Mesh sizing name - riteWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 4 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 4 Faces EGADS : Body 0 has 8 Edges EGADS : Body 0 has 4 Loops EGADS : Body 0 has 4 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 4 Faces EGADS : Body 1 has 8 Edges EGADS : Body 1 has 4 Loops EGADS : Body 1 has 4 Nodes EGADS : Body 2 is a SolidBody EGADS : Body 2 has 1 Shells EGADS : Body 2 has 100 Faces EGADS : Body 2 has 245 Edges EGADS : Body 2 has 102 Loops EGADS : Body 2 has 145 Nodes EGADS : Body 3 is a SolidBody EGADS : Body 3 has 1 Shells EGADS : Body 3 has 6 Faces EGADS : Body 3 has 12 Edges EGADS : Body 3 has 6 Loops EGADS : Body 3 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 5 2 3 EGADS : 2 Yes 0 0 1 0 5 1 4 EGADS : 3 Yes 0 0 1 0 5 1 4 EGADS : 4 Yes 0 0 1 0 5 2 3 EGADS : 5 Yes 1 0 1 0 5 6 7 EGADS : 6 Yes 1 0 1 0 5 5 8 EGADS : 7 Yes 1 0 1 0 5 5 8 EGADS : 8 Yes 1 0 1 0 5 6 7 EGADS : 9 Yes 2 0 1 0 4 10 14 32 107 EGADS : 10 Yes 2 0 1 0 4 9 11 39 108 EGADS : 11 Yes 2 0 1 0 4 10 12 39 108 EGADS : 12 Yes 2 0 1 0 4 11 13 39 108 EGADS : 13 Yes 2 0 1 0 4 12 14 32 107 EGADS : 14 Yes 2 0 1 0 4 9 13 32 107 EGADS : 15 Yes 2 0 1 0 4 16 17 18 19 EGADS : 16 Yes 2 0 1 0 4 15 17 20 21 22 EGADS : 23 24 EGADS : 17 Yes 2 0 1 0 4 15 16 18 22 EGADS : 18 Yes 2 0 1 0 4 15 17 22 25 EGADS : 19 Yes 2 0 1 0 4 15 20 25 26 EGADS : 20 Yes 2 0 1 0 4 16 19 21 23 24 EGADS : 26 27 EGADS : 21 Yes 2 0 1 0 4 16 20 EGADS : 22 Yes 2 0 1 0 4 16 17 18 27 EGADS : 23 Yes 2 0 1 0 1 16 20 24 28 29 EGADS : 30 EGADS : 24 Yes 2 0 1 0 1 16 20 23 29 31 EGADS : 32 33 EGADS : 25 Yes 2 0 1 0 4 18 19 26 27 EGADS : 26 Yes 2 0 1 0 4 19 20 25 27 EGADS : 27 Yes 2 0 1 0 4 20 22 25 26 EGADS : 28 Yes 2 0 1 0 1 23 29 31 34 35 EGADS : 36 EGADS : 29 Yes 2 0 1 0 1 23 24 28 31 EGADS : 30 Yes 2 0 1 0 1 23 33 36 37 38 EGADS : 31 Yes 2 0 1 0 1 24 28 29 34 35 EGADS : 39 40 EGADS : 32 Yes 2 0 1 0 4 9 13 14 24 39 41 EGADS : 33 Yes 2 0 1 0 1 24 30 40 EGADS : 34 Yes 2 0 1 0 4 28 31 35 42 43 EGADS : 44 45 EGADS : 35 Yes 2 0 1 0 4 28 31 34 42 46 EGADS : 47 48 EGADS : 36 Yes 2 0 1 0 1 28 30 40 49 50 EGADS : 37 Yes 2 0 1 0 4 30 38 51 52 53 EGADS : 54 EGADS : 38 Yes 2 0 1 0 4 30 37 55 56 57 EGADS : 58 EGADS : 39 Yes 2 0 1 0 4 10 11 12 31 32 EGADS : 41 EGADS : 40 Yes 2 0 1 0 1 31 33 36 EGADS : 41 Yes 2 0 1 0 4 32 39 EGADS : 42 Yes 2 0 1 0 4 34 35 EGADS : 43 Yes 2 0 1 0 4 34 44 48 59 EGADS : 44 Yes 2 0 1 0 4 34 43 45 59 EGADS : 45 Yes 2 0 1 0 4 34 44 46 59 EGADS : 46 Yes 2 0 1 0 4 35 45 47 60 EGADS : 47 Yes 2 0 1 0 4 35 46 48 60 EGADS : 48 Yes 2 0 1 0 4 35 43 47 60 EGADS : 49 Yes 2 0 1 0 4 36 50 61 62 63 EGADS : 64 EGADS : 50 Yes 2 0 1 0 4 36 49 65 66 67 EGADS : 68 EGADS : 51 Yes 2 0 1 0 4 37 52 58 69 EGADS : 52 Yes 2 0 1 0 4 37 51 53 69 EGADS : 53 Yes 2 0 1 0 4 37 52 56 69 EGADS : 54 Yes 2 0 1 0 4 37 55 70 71 72 EGADS : 73 74 75 76 EGADS : 55 Yes 2 0 1 0 4 38 54 76 77 78 EGADS : 79 80 81 82 EGADS : 56 Yes 2 0 1 0 4 38 53 57 83 EGADS : 57 Yes 2 0 1 0 4 38 56 58 83 EGADS : 58 Yes 2 0 1 0 4 38 51 57 83 EGADS : 59 Yes 2 0 1 0 4 43 44 45 60 EGADS : 60 Yes 2 0 1 0 4 46 47 48 59 EGADS : 61 Yes 2 0 1 0 4 49 68 84 85 86 EGADS : 87 88 89 90 EGADS : 62 Yes 2 0 1 0 4 49 63 67 91 EGADS : 63 Yes 2 0 1 0 4 49 62 64 91 EGADS : 64 Yes 2 0 1 0 4 49 63 65 91 EGADS : 65 Yes 2 0 1 0 4 50 64 66 92 EGADS : 66 Yes 2 0 1 0 4 50 65 67 92 EGADS : 67 Yes 2 0 1 0 4 50 62 66 92 EGADS : 68 Yes 2 0 1 0 4 50 61 84 93 94 EGADS : 95 96 97 98 EGADS : 69 Yes 2 0 1 0 4 51 52 53 83 EGADS : 70 Yes 2 0 1 0 4 54 71 82 99 EGADS : 71 Yes 2 0 1 0 4 54 70 72 99 EGADS : 72 Yes 2 0 1 0 4 54 71 80 99 EGADS : 73 Yes 2 0 1 0 4 54 74 79 100 EGADS : 74 Yes 2 0 1 0 4 54 73 75 100 EGADS : 75 Yes 2 0 1 0 4 54 74 77 100 EGADS : 76 Yes 2 0 1 0 4 54 55 EGADS : 77 Yes 2 0 1 0 4 55 75 78 101 EGADS : 78 Yes 2 0 1 0 4 55 77 79 101 EGADS : 79 Yes 2 0 1 0 4 55 73 78 101 EGADS : 80 Yes 2 0 1 0 4 55 72 81 102 EGADS : 81 Yes 2 0 1 0 4 55 80 82 102 EGADS : 82 Yes 2 0 1 0 4 55 70 81 102 EGADS : 83 Yes 2 0 1 0 4 56 57 58 69 EGADS : 84 Yes 2 0 1 0 4 61 68 EGADS : 85 Yes 2 0 1 0 4 61 86 98 103 EGADS : 86 Yes 2 0 1 0 4 61 85 87 103 EGADS : 87 Yes 2 0 1 0 4 61 86 96 103 EGADS : 88 Yes 2 0 1 0 4 61 89 95 104 EGADS : 89 Yes 2 0 1 0 4 61 88 90 104 EGADS : 90 Yes 2 0 1 0 4 61 89 93 104 EGADS : 91 Yes 2 0 1 0 4 62 63 64 92 EGADS : 92 Yes 2 0 1 0 4 65 66 67 91 EGADS : 93 Yes 2 0 1 0 4 68 90 94 105 EGADS : 94 Yes 2 0 1 0 4 68 93 95 105 EGADS : 95 Yes 2 0 1 0 4 68 88 94 105 EGADS : 96 Yes 2 0 1 0 4 68 87 97 106 EGADS : 97 Yes 2 0 1 0 4 68 96 98 106 EGADS : 98 Yes 2 0 1 0 4 68 85 97 106 EGADS : 99 Yes 2 0 1 0 4 70 71 72 102 EGADS : 100 Yes 2 0 1 0 4 73 74 75 101 EGADS : 101 Yes 2 0 1 0 4 77 78 79 100 EGADS : 102 Yes 2 0 1 0 4 80 81 82 99 EGADS : 103 Yes 2 0 1 0 4 85 86 87 106 EGADS : 104 Yes 2 0 1 0 4 88 89 90 105 EGADS : 105 Yes 2 0 1 0 4 93 94 95 104 EGADS : 106 Yes 2 0 1 0 4 96 97 98 103 EGADS : 107 Yes 2 0 1 0 4 9 13 14 108 EGADS : 108 Yes 2 0 1 0 4 10 11 12 107 EGADS : 109 Yes 3 0 1 NA NA 111 112 113 114 EGADS : 110 Yes 3 0 1 NA NA 111 112 113 114 EGADS : 111 Yes 3 0 1 NA NA 109 110 113 114 EGADS : 112 Yes 3 0 1 NA NA 109 110 113 114 EGADS : 113 Yes 3 0 1 NA NA 109 110 111 112 EGADS : 114 Yes 3 0 1 NA NA 109 110 111 112 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 3 2 -4 EGADS : 2 -2 5 1 -6 EGADS : 3 7 4 -8 -3 EGADS : 4 8 6 -7 -5 EGADS : 5 9 12 -10 -11 EGADS : 6 10 14 -9 -13 EGADS : 7 -15 11 16 -12 EGADS : 8 -16 13 15 -14 EGADS : 9 -17 20 19 -18 EGADS : 10 -21 18 23 -22 EGADS : 11 -24 22 26 -25 EGADS : 12 27 25 -28 -29 EGADS : 13 30 29 -31 -32 EGADS : 14 33 32 -34 -20 EGADS : 15 35 36 -37 -38 EGADS : 16 39 40 -41 42 -43 -35 -44 45 46 EGADS : 17 43 47 -48 -36 EGADS : 18 -49 37 48 -50 EGADS : 19 51 38 -52 -53 EGADS : 20 44 -51 54 55 41 56 -39 57 58 EGADS : 21 -56 -40 EGADS : 22 -42 59 50 -47 EGADS : 23 -60 64 63 -45 -58 62 -61 EGADS : 24 -63 69 68 67 66 -65 -62 -57 -46 EGADS : 25 49 -70 -71 52 EGADS : 26 -54 53 71 -72 EGADS : 27 -55 72 70 -59 EGADS : 28 -73 78 60 -77 -76 75 74 EGADS : 29 61 65 79 77 EGADS : 30 -80 82 81 -64 -83 -84 EGADS : 31 -68 88 73 87 86 76 -79 -66 85 EGADS : 32 -89 -67 92 -91 -90 -30 -33 17 EGADS : 33 -81 93 94 -69 EGADS : 34 -95 -87 -74 101 100 99 -98 97 -96 EGADS : 35 -101 -75 -86 95 -105 -97 -104 -103 102 EGADS : 36 -106 107 80 -78 108 109 EGADS : 37 110 -111 112 113 114 115 -116 83 EGADS : 38 116 117 -114 118 -119 -120 -110 84 EGADS : 39 -92 -85 89 21 24 -27 90 -121 EGADS : 40 -94 122 106 -88 EGADS : 41 91 121 EGADS : 42 105 96 EGADS : 43 98 123 -124 -125 EGADS : 44 -99 127 126 -123 EGADS : 45 -100 129 128 -127 EGADS : 46 -102 131 130 -129 EGADS : 47 103 132 -133 -131 EGADS : 48 104 125 -134 -132 EGADS : 49 -135 -108 141 140 139 -138 137 -136 EGADS : 50 -141 -109 135 -145 -137 -144 -143 142 EGADS : 51 111 146 -147 -148 EGADS : 52 -112 148 150 -149 EGADS : 53 -113 149 152 -151 EGADS : 54 153 -154 155 156 157 -158 159 160 161 162 -163 -115 EGADS : 55 163 164 -161 165 -166 -167 -157 168 -169 -170 -153 -117 EGADS : 56 -118 151 172 -171 EGADS : 57 119 171 -173 -174 EGADS : 58 120 174 -175 -146 EGADS : 59 176 124 -126 -128 EGADS : 60 -176 -130 133 134 EGADS : 61 -177 136 187 186 185 -184 183 182 181 -180 179 -178 EGADS : 62 138 188 -189 -190 EGADS : 63 -139 192 191 -188 EGADS : 64 -140 194 193 -192 EGADS : 65 -142 196 195 -194 EGADS : 66 143 197 -198 -196 EGADS : 67 144 190 -199 -197 EGADS : 68 -187 145 177 -206 -179 -205 -204 203 -183 -202 -201 200 EGADS : 69 207 -152 -150 147 EGADS : 70 154 208 -209 -210 EGADS : 71 -155 210 212 -211 EGADS : 72 -156 211 214 -213 EGADS : 73 158 215 -216 -217 EGADS : 74 -159 217 219 -218 EGADS : 75 -160 218 221 -220 EGADS : 76 -162 -164 EGADS : 77 -165 220 223 -222 EGADS : 78 166 222 -224 -225 EGADS : 79 167 225 -226 -215 EGADS : 80 -168 213 228 -227 EGADS : 81 169 227 -229 -230 EGADS : 82 170 230 -231 -208 EGADS : 83 175 173 -172 -207 EGADS : 84 206 178 EGADS : 85 180 232 -233 -234 EGADS : 86 -181 236 235 -232 EGADS : 87 -182 238 237 -236 EGADS : 88 184 239 -240 -241 EGADS : 89 -185 243 242 -239 EGADS : 90 -186 245 244 -243 EGADS : 91 -193 246 189 -191 EGADS : 92 -246 -195 198 199 EGADS : 93 -200 248 247 -245 EGADS : 94 201 249 -250 -248 EGADS : 95 202 241 -251 -249 EGADS : 96 -203 253 252 -238 EGADS : 97 204 254 -255 -253 EGADS : 98 205 234 -256 -254 EGADS : 99 257 -214 -212 209 EGADS : 100 -221 -219 216 258 EGADS : 101 -258 226 224 -223 EGADS : 102 231 229 -228 -257 EGADS : 103 -237 259 233 -235 EGADS : 104 -244 260 240 -242 EGADS : 105 -260 -247 250 251 EGADS : 106 -259 -252 255 256 EGADS : 107 -261 -19 34 31 EGADS : 108 -23 261 28 -26 EGADS : 109 262 263 -264 -265 EGADS : 110 -266 269 268 -267 EGADS : 111 270 266 -271 -262 EGADS : 112 -272 264 273 -268 EGADS : 113 265 272 -269 -270 EGADS : 114 -263 271 267 -273 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : 17 17 EGADS : 18 18 EGADS : 19 19 EGADS : 20 20 EGADS : 21 21 EGADS : 22 22 EGADS : 23 23 EGADS : 24 24 EGADS : 25 25 EGADS : 26 26 EGADS : 27 27 EGADS : 28 28 EGADS : 29 29 EGADS : 30 30 31 EGADS : 31 32 EGADS : 32 33 EGADS : 33 34 EGADS : 34 35 EGADS : 35 36 EGADS : 36 37 38 EGADS : 37 39 EGADS : 38 40 EGADS : 39 41 EGADS : 40 42 EGADS : 41 43 EGADS : 42 44 EGADS : 43 45 EGADS : 44 46 EGADS : 45 47 EGADS : 46 48 EGADS : 47 49 EGADS : 48 50 EGADS : 49 51 EGADS : 50 52 EGADS : 51 53 EGADS : 52 54 EGADS : 53 55 EGADS : 54 56 EGADS : 55 57 EGADS : 56 58 EGADS : 57 59 EGADS : 58 60 EGADS : 59 61 EGADS : 60 62 EGADS : 61 63 EGADS : 62 64 EGADS : 63 65 EGADS : 64 66 EGADS : 65 67 EGADS : 66 68 EGADS : 67 69 EGADS : 68 70 EGADS : 69 71 EGADS : 70 72 EGADS : 71 73 EGADS : 72 74 EGADS : 73 75 EGADS : 74 76 EGADS : 75 77 EGADS : 76 78 EGADS : 77 79 EGADS : 78 80 EGADS : 79 81 EGADS : 80 82 EGADS : 81 83 EGADS : 82 84 EGADS : 83 85 EGADS : 84 86 EGADS : 85 87 EGADS : 86 88 EGADS : 87 89 EGADS : 88 90 EGADS : 89 91 EGADS : 90 92 EGADS : 91 93 EGADS : 92 94 EGADS : 93 95 EGADS : 94 96 EGADS : 95 97 EGADS : 96 98 EGADS : 97 99 EGADS : 98 100 EGADS : 99 101 EGADS : 100 102 EGADS : 101 103 EGADS : 102 104 EGADS : 103 105 EGADS : 104 106 EGADS : 105 107 EGADS : 106 108 EGADS : 107 109 EGADS : 108 110 EGADS : 109 111 EGADS : 110 112 EGADS : 111 113 EGADS : 112 114 EGADS : 113 115 EGADS : 114 116 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 3 2 -4 EGADS : 2 Yes -2 5 1 -6 EGADS : 3 Yes 7 4 -8 -3 EGADS : 4 Yes 8 6 -7 -5 EGADS : 5 Yes 9 12 -10 -11 EGADS : 6 Yes 10 14 -9 -13 EGADS : 7 Yes -15 11 16 -12 EGADS : 8 Yes -16 13 15 -14 EGADS : 9 Yes -17 20 19 -18 EGADS : 10 Yes -21 18 23 -22 EGADS : 11 Yes -24 22 26 -25 EGADS : 12 Yes 27 25 -28 -29 EGADS : 13 Yes 30 29 -31 -32 EGADS : 14 Yes 33 32 -34 -20 EGADS : 15 Yes 35 36 -37 -38 EGADS : 16 Yes 39 40 -41 42 -43 -35 -44 45 46 EGADS : 17 Yes 43 47 -48 -36 EGADS : 18 Yes -49 37 48 -50 EGADS : 19 Yes 51 38 -52 -53 EGADS : 20 Yes 44 -51 54 55 41 56 -39 57 58 EGADS : 21 Yes -56 -40 EGADS : 22 Yes -42 59 50 -47 EGADS : 23 Yes -60 64 63 -45 -58 62 -61 EGADS : 24 Yes -63 69 68 67 66 -65 -62 -57 -46 EGADS : 25 Yes 49 -70 -71 52 EGADS : 26 Yes -54 53 71 -72 EGADS : 27 Yes -55 72 70 -59 EGADS : 28 Yes -73 78 60 -77 -76 75 74 EGADS : 29 Yes 61 65 79 77 EGADS : 30 Yes -80 82 81 -64 EGADS : 31 Yes -83 -84 EGADS : 32 Yes -68 88 73 87 86 76 -79 -66 85 EGADS : 33 Yes -89 -67 92 -91 -90 -30 -33 17 EGADS : 34 Yes -81 93 94 -69 EGADS : 35 Yes -95 -87 -74 101 100 99 -98 97 -96 EGADS : 36 Yes -101 -75 -86 95 -105 -97 -104 -103 102 EGADS : 37 Yes -106 107 80 -78 EGADS : 38 Yes 108 109 EGADS : 39 Yes 110 -111 112 113 114 115 -116 83 EGADS : 40 Yes 116 117 -114 118 -119 -120 -110 84 EGADS : 41 Yes -92 -85 89 21 24 -27 90 -121 EGADS : 42 Yes -94 122 106 -88 EGADS : 43 Yes 91 121 EGADS : 44 Yes 105 96 EGADS : 45 Yes 98 123 -124 -125 EGADS : 46 Yes -99 127 126 -123 EGADS : 47 Yes -100 129 128 -127 EGADS : 48 Yes -102 131 130 -129 EGADS : 49 Yes 103 132 -133 -131 EGADS : 50 Yes 104 125 -134 -132 EGADS : 51 Yes -135 -108 141 140 139 -138 137 -136 EGADS : 52 Yes -141 -109 135 -145 -137 -144 -143 142 EGADS : 53 Yes 111 146 -147 -148 EGADS : 54 Yes -112 148 150 -149 EGADS : 55 Yes -113 149 152 -151 EGADS : 56 Yes 153 -154 155 156 157 -158 159 160 161 162 -163 -115 EGADS : 57 Yes 163 164 -161 165 -166 -167 -157 168 -169 -170 -153 EGADS : -117 EGADS : 58 Yes -118 151 172 -171 EGADS : 59 Yes 119 171 -173 -174 EGADS : 60 Yes 120 174 -175 -146 EGADS : 61 Yes 176 124 -126 -128 EGADS : 62 Yes -176 -130 133 134 EGADS : 63 Yes -177 136 187 186 185 -184 183 182 181 -180 179 -178 EGADS : 64 Yes 138 188 -189 -190 EGADS : 65 Yes -139 192 191 -188 EGADS : 66 Yes -140 194 193 -192 EGADS : 67 Yes -142 196 195 -194 EGADS : 68 Yes 143 197 -198 -196 EGADS : 69 Yes 144 190 -199 -197 EGADS : 70 Yes -187 145 177 -206 -179 -205 -204 203 -183 -202 -201 EGADS : 200 EGADS : 71 Yes 207 -152 -150 147 EGADS : 72 Yes 154 208 -209 -210 EGADS : 73 Yes -155 210 212 -211 EGADS : 74 Yes -156 211 214 -213 EGADS : 75 Yes 158 215 -216 -217 EGADS : 76 Yes -159 217 219 -218 EGADS : 77 Yes -160 218 221 -220 EGADS : 78 Yes -162 -164 EGADS : 79 Yes -165 220 223 -222 EGADS : 80 Yes 166 222 -224 -225 EGADS : 81 Yes 167 225 -226 -215 EGADS : 82 Yes -168 213 228 -227 EGADS : 83 Yes 169 227 -229 -230 EGADS : 84 Yes 170 230 -231 -208 EGADS : 85 Yes 175 173 -172 -207 EGADS : 86 Yes 206 178 EGADS : 87 Yes 180 232 -233 -234 EGADS : 88 Yes -181 236 235 -232 EGADS : 89 Yes -182 238 237 -236 EGADS : 90 Yes 184 239 -240 -241 EGADS : 91 Yes -185 243 242 -239 EGADS : 92 Yes -186 245 244 -243 EGADS : 93 Yes -193 246 189 -191 EGADS : 94 Yes -246 -195 198 199 EGADS : 95 Yes -200 248 247 -245 EGADS : 96 Yes 201 249 -250 -248 EGADS : 97 Yes 202 241 -251 -249 EGADS : 98 Yes -203 253 252 -238 EGADS : 99 Yes 204 254 -255 -253 EGADS : 100 Yes 205 234 -256 -254 EGADS : 101 Yes 257 -214 -212 209 EGADS : 102 Yes -221 -219 216 258 EGADS : 103 Yes -258 226 224 -223 EGADS : 104 Yes 231 229 -228 -257 EGADS : 105 Yes -237 259 233 -235 EGADS : 106 Yes -244 260 240 -242 EGADS : 107 Yes -260 -247 250 251 EGADS : 108 Yes -259 -252 255 256 EGADS : 109 Yes -261 -19 34 31 EGADS : 110 Yes -23 261 28 -26 EGADS : 111 Yes 262 263 -264 -265 EGADS : 112 Yes -266 269 268 -267 EGADS : 113 Yes 270 266 -271 -262 EGADS : 114 Yes -272 264 273 -268 EGADS : 115 Yes 265 272 -269 -270 EGADS : 116 Yes -263 271 267 -273 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 2 EGADS : 2 0 Yes 3 4 1 1 2 EGADS : 3 0 Yes 1 3 1 1 3 EGADS : 4 0 Yes 2 4 1 1 3 EGADS : 5 0 Yes 3 1 1 2 4 EGADS : 6 0 Yes 4 2 1 2 4 EGADS : 7 0 Yes 1 2 1 3 4 EGADS : 8 0 Yes 3 4 1 3 4 EGADS : 9 1 Yes 5 6 1 5 6 EGADS : 10 1 Yes 7 8 1 5 6 EGADS : 11 1 Yes 5 7 1 5 7 EGADS : 12 1 Yes 6 8 1 5 7 EGADS : 13 1 Yes 7 5 1 6 8 EGADS : 14 1 Yes 8 6 1 6 8 EGADS : 15 1 Yes 5 6 1 7 8 EGADS : 16 1 Yes 7 8 1 7 8 EGADS : 17 2 Yes 9 10 1 9 32 EGADS : 18 2 Yes 10 11 1 9 10 EGADS : 19 2 Yes 12 11 1 9 107 EGADS : 20 2 Yes 9 12 1 9 14 EGADS : 21 2 Yes 10 13 1 10 39 EGADS : 22 2 Yes 13 14 1 10 11 EGADS : 23 2 Yes 11 14 1 10 108 EGADS : 24 2 Yes 13 15 1 11 39 EGADS : 25 2 Yes 15 16 1 11 12 EGADS : 26 2 Yes 14 16 1 11 108 EGADS : 27 2 Yes 17 15 1 12 39 EGADS : 28 2 Yes 18 16 1 12 108 EGADS : 29 2 Yes 17 18 1 12 13 EGADS : 30 2 Yes 19 17 1 13 32 EGADS : 31 2 Yes 20 18 1 13 107 EGADS : 32 2 Yes 19 20 1 13 14 EGADS : 33 2 Yes 9 19 1 14 32 EGADS : 34 2 Yes 12 20 1 14 107 EGADS : 35 2 Yes 21 22 1 15 16 EGADS : 36 2 Yes 22 23 1 15 17 EGADS : 37 2 Yes 24 23 1 15 18 EGADS : 38 2 Yes 21 24 1 15 19 EGADS : 39 2 Yes 25 26 1 16 20 EGADS : 40 2 Yes 26 27 1 16 21 EGADS : 41 2 Yes 28 27 1 16 20 EGADS : 42 2 Yes 28 29 1 16 22 EGADS : 43 2 Yes 22 29 1 16 17 EGADS : 44 2 Yes 30 21 1 16 20 EGADS : 45 2 Yes 30 31 1 16 23 EGADS : 46 2 Yes 31 25 1 16 24 EGADS : 47 2 Yes 29 32 1 17 22 EGADS : 48 2 Yes 23 32 1 17 18 EGADS : 49 2 Yes 24 33 1 18 25 EGADS : 50 2 Yes 33 32 1 18 22 EGADS : 51 2 Yes 34 21 1 19 20 EGADS : 52 2 Yes 35 24 1 19 25 EGADS : 53 2 Yes 34 35 1 19 26 EGADS : 54 2 Yes 34 36 1 20 26 EGADS : 55 2 Yes 36 28 1 20 27 EGADS : 56 2 Yes 27 26 1 20 21 EGADS : 57 2 Yes 25 37 1 20 24 EGADS : 58 2 Yes 37 30 1 20 23 EGADS : 59 2 Yes 28 33 1 22 27 EGADS : 60 2 Yes 38 39 1 23 28 EGADS : 61 2 Yes 39 40 1 23 29 EGADS : 62 2 Yes 37 40 1 23 24 EGADS : 63 2 Yes 41 31 1 23 24 EGADS : 64 2 Yes 38 41 1 23 30 EGADS : 65 2 Yes 40 42 1 24 29 EGADS : 66 2 Yes 43 42 1 24 31 EGADS : 67 2 Yes 44 43 1 24 32 EGADS : 68 2 Yes 45 44 1 24 31 EGADS : 69 2 Yes 41 45 1 24 33 EGADS : 70 2 Yes 46 33 1 25 27 EGADS : 71 2 Yes 35 46 1 25 26 EGADS : 72 2 Yes 36 46 1 26 27 EGADS : 73 2 Yes 47 48 1 28 31 EGADS : 74 2 Yes 49 48 1 28 34 EGADS : 75 2 Yes 50 49 1 28 35 EGADS : 76 2 Yes 50 51 1 28 31 EGADS : 77 2 Yes 51 39 1 28 29 EGADS : 78 2 Yes 47 38 1 28 36 EGADS : 79 2 Yes 42 51 1 29 31 EGADS : 80 2 Yes 52 38 1 30 36 EGADS : 81 2 Yes 52 41 1 30 33 EGADS : 82 2 DEGEN 52 52 - 30 EGADS : 83 2 Yes 53 54 1 30 37 EGADS : 84 2 Yes 54 53 1 30 38 EGADS : 85 2 Yes 43 44 1 31 39 EGADS : 86 2 Yes 55 50 1 31 35 EGADS : 87 2 Yes 48 55 1 31 34 EGADS : 88 2 Yes 45 47 1 31 40 EGADS : 89 2 Yes 43 10 1 32 39 EGADS : 90 2 Yes 17 56 1 32 39 EGADS : 91 2 Yes 56 57 1 32 41 EGADS : 92 2 Yes 44 57 1 32 39 EGADS : 93 2 DEGEN 52 52 - 33 EGADS : 94 2 Yes 52 45 1 33 40 EGADS : 95 2 Yes 55 58 1 34 35 EGADS : 96 2 Yes 58 59 1 34 42 EGADS : 97 2 Yes 60 59 1 34 35 EGADS : 98 2 Yes 60 61 1 34 43 EGADS : 99 2 Yes 62 61 1 34 44 EGADS : 100 2 Yes 63 62 1 34 45 EGADS : 101 2 Yes 49 63 1 34 35 EGADS : 102 2 Yes 64 63 1 35 46 EGADS : 103 2 Yes 64 65 1 35 47 EGADS : 104 2 Yes 65 60 1 35 48 EGADS : 105 2 Yes 59 58 1 35 42 EGADS : 106 2 Yes 52 47 1 36 40 EGADS : 107 2 DEGEN 52 52 - 36 EGADS : 108 2 Yes 66 67 1 36 49 EGADS : 109 2 Yes 67 66 1 36 50 EGADS : 110 2 Yes 54 68 1 37 38 EGADS : 111 2 Yes 69 68 1 37 51 EGADS : 112 2 Yes 69 70 1 37 52 EGADS : 113 2 Yes 70 71 1 37 53 EGADS : 114 2 Yes 71 72 1 37 38 EGADS : 115 2 Yes 72 73 1 37 54 EGADS : 116 2 Yes 53 73 1 37 38 EGADS : 117 2 Yes 73 72 1 38 55 EGADS : 118 2 Yes 71 74 1 38 56 EGADS : 119 2 Yes 75 74 1 38 57 EGADS : 120 2 Yes 68 75 1 38 58 EGADS : 121 2 Yes 57 56 1 39 41 EGADS : 122 2 DEGEN 52 52 - 40 EGADS : 123 2 Yes 61 76 1 43 44 EGADS : 124 2 Yes 77 76 1 43 59 EGADS : 125 2 Yes 60 77 1 43 48 EGADS : 126 2 Yes 78 76 1 44 59 EGADS : 127 2 Yes 62 78 1 44 45 EGADS : 128 2 Yes 79 78 1 45 59 EGADS : 129 2 Yes 63 79 1 45 46 EGADS : 130 2 Yes 80 79 1 46 60 EGADS : 131 2 Yes 64 80 1 46 47 EGADS : 132 2 Yes 65 81 1 47 48 EGADS : 133 2 Yes 80 81 1 47 60 EGADS : 134 2 Yes 81 77 1 48 60 EGADS : 135 2 Yes 67 82 1 49 50 EGADS : 136 2 Yes 82 83 1 49 61 EGADS : 137 2 Yes 84 83 1 49 50 EGADS : 138 2 Yes 84 85 1 49 62 EGADS : 139 2 Yes 86 85 1 49 63 EGADS : 140 2 Yes 87 86 1 49 64 EGADS : 141 2 Yes 66 87 1 49 50 EGADS : 142 2 Yes 88 87 1 50 65 EGADS : 143 2 Yes 88 89 1 50 66 EGADS : 144 2 Yes 89 84 1 50 67 EGADS : 145 2 Yes 83 82 1 50 68 EGADS : 146 2 Yes 68 90 1 51 58 EGADS : 147 2 Yes 91 90 1 51 69 EGADS : 148 2 Yes 69 91 1 51 52 EGADS : 149 2 Yes 70 92 1 52 53 EGADS : 150 2 Yes 91 92 1 52 69 EGADS : 151 2 Yes 71 93 1 53 56 EGADS : 152 2 Yes 92 93 1 53 69 EGADS : 153 2 Yes 72 94 1 54 55 EGADS : 154 2 Yes 95 94 1 54 70 EGADS : 155 2 Yes 95 96 1 54 71 EGADS : 156 2 Yes 96 97 1 54 72 EGADS : 157 2 Yes 97 98 1 54 55 EGADS : 158 2 Yes 99 98 1 54 73 EGADS : 159 2 Yes 99 100 1 54 74 EGADS : 160 2 Yes 100 101 1 54 75 EGADS : 161 2 Yes 101 102 1 54 55 EGADS : 162 2 Yes 102 103 1 54 76 EGADS : 163 2 Yes 73 103 1 54 55 EGADS : 164 2 Yes 103 102 1 55 76 EGADS : 165 2 Yes 101 104 1 55 77 EGADS : 166 2 Yes 105 104 1 55 78 EGADS : 167 2 Yes 98 105 1 55 79 EGADS : 168 2 Yes 97 106 1 55 80 EGADS : 169 2 Yes 107 106 1 55 81 EGADS : 170 2 Yes 94 107 1 55 82 EGADS : 171 2 Yes 74 108 1 56 57 EGADS : 172 2 Yes 93 108 1 56 83 EGADS : 173 2 Yes 109 108 1 57 83 EGADS : 174 2 Yes 75 109 1 57 58 EGADS : 175 2 Yes 90 109 1 58 83 EGADS : 176 2 Yes 79 77 1 59 60 EGADS : 177 2 Yes 82 110 1 61 68 EGADS : 178 2 Yes 110 111 1 61 84 EGADS : 179 2 Yes 112 111 1 61 68 EGADS : 180 2 Yes 112 113 1 61 85 EGADS : 181 2 Yes 114 113 1 61 86 EGADS : 182 2 Yes 115 114 1 61 87 EGADS : 183 2 Yes 116 115 1 61 68 EGADS : 184 2 Yes 116 117 1 61 88 EGADS : 185 2 Yes 118 117 1 61 89 EGADS : 186 2 Yes 119 118 1 61 90 EGADS : 187 2 Yes 83 119 1 61 68 EGADS : 188 2 Yes 85 120 1 62 63 EGADS : 189 2 Yes 121 120 1 62 91 EGADS : 190 2 Yes 84 121 1 62 67 EGADS : 191 2 Yes 122 120 1 63 91 EGADS : 192 2 Yes 86 122 1 63 64 EGADS : 193 2 Yes 123 122 1 64 91 EGADS : 194 2 Yes 87 123 1 64 65 EGADS : 195 2 Yes 124 123 1 65 92 EGADS : 196 2 Yes 88 124 1 65 66 EGADS : 197 2 Yes 89 125 1 66 67 EGADS : 198 2 Yes 124 125 1 66 92 EGADS : 199 2 Yes 125 121 1 67 92 EGADS : 200 2 Yes 126 119 1 68 93 EGADS : 201 2 Yes 126 127 1 68 94 EGADS : 202 2 Yes 127 116 1 68 95 EGADS : 203 2 Yes 128 115 1 68 96 EGADS : 204 2 Yes 128 129 1 68 97 EGADS : 205 2 Yes 129 112 1 68 98 EGADS : 206 2 Yes 111 110 1 68 84 EGADS : 207 2 Yes 90 93 1 69 83 EGADS : 208 2 Yes 94 130 1 70 82 EGADS : 209 2 Yes 131 130 1 70 99 EGADS : 210 2 Yes 95 131 1 70 71 EGADS : 211 2 Yes 96 132 1 71 72 EGADS : 212 2 Yes 131 132 1 71 99 EGADS : 213 2 Yes 97 133 1 72 80 EGADS : 214 2 Yes 132 133 1 72 99 EGADS : 215 2 Yes 98 134 1 73 79 EGADS : 216 2 Yes 135 134 1 73 100 EGADS : 217 2 Yes 99 135 1 73 74 EGADS : 218 2 Yes 100 136 1 74 75 EGADS : 219 2 Yes 135 136 1 74 100 EGADS : 220 2 Yes 101 137 1 75 77 EGADS : 221 2 Yes 136 137 1 75 100 EGADS : 222 2 Yes 104 138 1 77 78 EGADS : 223 2 Yes 137 138 1 77 101 EGADS : 224 2 Yes 139 138 1 78 101 EGADS : 225 2 Yes 105 139 1 78 79 EGADS : 226 2 Yes 134 139 1 79 101 EGADS : 227 2 Yes 106 140 1 80 81 EGADS : 228 2 Yes 133 140 1 80 102 EGADS : 229 2 Yes 141 140 1 81 102 EGADS : 230 2 Yes 107 141 1 81 82 EGADS : 231 2 Yes 130 141 1 82 102 EGADS : 232 2 Yes 113 142 1 85 86 EGADS : 233 2 Yes 143 142 1 85 103 EGADS : 234 2 Yes 112 143 1 85 98 EGADS : 235 2 Yes 144 142 1 86 103 EGADS : 236 2 Yes 114 144 1 86 87 EGADS : 237 2 Yes 145 144 1 87 103 EGADS : 238 2 Yes 115 145 1 87 96 EGADS : 239 2 Yes 117 146 1 88 89 EGADS : 240 2 Yes 147 146 1 88 104 EGADS : 241 2 Yes 116 147 1 88 95 EGADS : 242 2 Yes 148 146 1 89 104 EGADS : 243 2 Yes 118 148 1 89 90 EGADS : 244 2 Yes 149 148 1 90 104 EGADS : 245 2 Yes 119 149 1 90 93 EGADS : 246 2 Yes 123 121 1 91 92 EGADS : 247 2 Yes 150 149 1 93 105 EGADS : 248 2 Yes 126 150 1 93 94 EGADS : 249 2 Yes 127 151 1 94 95 EGADS : 250 2 Yes 150 151 1 94 105 EGADS : 251 2 Yes 151 147 1 95 105 EGADS : 252 2 Yes 152 145 1 96 106 EGADS : 253 2 Yes 128 152 1 96 97 EGADS : 254 2 Yes 129 153 1 97 98 EGADS : 255 2 Yes 152 153 1 97 106 EGADS : 256 2 Yes 153 143 1 98 106 EGADS : 257 2 Yes 130 133 1 99 102 EGADS : 258 2 Yes 134 137 1 100 101 EGADS : 259 2 Yes 145 143 1 103 106 EGADS : 260 2 Yes 149 147 1 104 105 EGADS : 261 2 Yes 11 18 1 107 108 EGADS : 262 3 Yes 155 154 NA 109 111 EGADS : 263 3 Yes 154 156 NA 109 114 EGADS : 264 3 Yes 157 156 NA 109 112 EGADS : 265 3 Yes 155 157 NA 109 113 EGADS : 266 3 Yes 159 158 NA 110 111 EGADS : 267 3 Yes 158 160 NA 110 114 EGADS : 268 3 Yes 161 160 NA 110 112 EGADS : 269 3 Yes 159 161 NA 110 113 EGADS : 270 3 Yes 155 159 NA 111 113 EGADS : 271 3 Yes 154 158 NA 111 114 EGADS : 272 3 Yes 157 161 NA 112 113 EGADS : 273 3 Yes 156 160 NA 112 114 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 90.5173952 0 0 EGADS : 2 Yes 90.5173952 0 0 EGADS : 3 Yes 60.5173952 0 0 EGADS : 4 Yes 60.5173952 0 0 EGADS : 5 Yes 90.5173952 29.3018771 0 EGADS : 6 Yes 90.5173952 29.3018771 0 EGADS : 7 Yes 60.5173952 29.3018771 0 EGADS : 8 Yes 60.5173952 29.3018771 0 EGADS : 9 Yes 155.279418 0.556318046 17.8486974 EGADS : 10 Yes 162.754076 0 17.8179957 EGADS : 11 Yes 162.923819 0 18.2706428 EGADS : 12 Yes 156.044413 0.521348839 18.2706428 EGADS : 13 Yes 155.279418 0 17.8486974 EGADS : 14 Yes 156.044413 0 18.2706428 EGADS : 15 Yes 166.073363 0 35.1119946 EGADS : 16 Yes 166.308339 0 34.6929244 EGADS : 17 Yes 169.251074 0 35.1433216 EGADS : 18 Yes 169.082175 0 34.6929244 EGADS : 19 Yes 166.073363 0.227596794 35.1119946 EGADS : 20 Yes 166.308339 0.210212312 34.6929244 EGADS : 21 Yes 162.505711 6.6926087 7.42255789 EGADS : 22 Yes 153.264796 6.72114619 6.73834001 EGADS : 23 Yes 153.930225 7.199099 6.86796425 EGADS : 24 Yes 162.623387 7.31455844 6.87508685 EGADS : 25 Yes 139.227902 5.03861756 7.07099122 EGADS : 26 Yes 165.02399 35.781198 13.6055284 EGADS : 27 Yes 173.282633 35.781198 13.6055284 EGADS : 28 Yes 172.798165 34.4735419 13.3275775 EGADS : 29 Yes 168.724656 34.4225125 13.0211892 EGADS : 30 Yes 160.457816 1.16501909 6.24763245 EGADS : 31 Yes 152.092394 3.29252447 6.00142548 EGADS : 32 Yes 168.960236 34.0035224 12.9505074 EGADS : 33 Yes 172.609156 34.051986 12.953497 EGADS : 34 Yes 153.264796 6.72114619 8.11890743 EGADS : 35 Yes 154.029174 7.14485531 8.17706386 EGADS : 36 Yes 168.724656 34.4225125 13.6122726 EGADS : 37 Yes 156.577382 2.32417494 6.86784347 EGADS : 38 Yes 121.026192 0 0 EGADS : 39 Yes 165.026192 0 7 EGADS : 40 Yes 165.026192 0.5 8.5 EGADS : 41 Yes 121.026192 10 0 EGADS : 42 Yes 165.026192 0 10 EGADS : 43 Yes 159.822328 0 10 EGADS : 44 Yes 137.454662 0 10 EGADS : 45 Yes 121.026192 0 10 EGADS : 46 Yes 169.00177 33.9807538 13.4999966 EGADS : 47 Yes 121.026192 0 0 EGADS : 48 Yes 152.092394 0 6.00142548 EGADS : 49 Yes 160.457816 0 6.24763245 EGADS : 50 Yes 156.577382 0 6.86784347 EGADS : 51 Yes 165.026192 0 8.5 EGADS : 52 Yes 0 0 0 EGADS : 53 Yes 54.9020417 7.00084115 0 EGADS : 54 Yes 97.361045 7.90366896 0 EGADS : 55 Yes 139.227902 0 7.07099122 EGADS : 56 Yes 169.38016 0 35.487551 EGADS : 57 Yes 162.942213 0 35.487551 EGADS : 58 Yes 165.02399 0 13.6055284 EGADS : 59 Yes 173.282633 0 13.6055284 EGADS : 60 Yes 172.798165 0 13.3275775 EGADS : 61 Yes 168.724656 0 13.0211892 EGADS : 62 Yes 153.264796 0 6.73834001 EGADS : 63 Yes 162.505711 0 7.42255789 EGADS : 64 Yes 153.264796 0 8.11890743 EGADS : 65 Yes 168.724656 0 13.6122726 EGADS : 66 Yes 97.361045 0 0 EGADS : 67 Yes 54.9020417 0 0 EGADS : 68 Yes 97.4729837 13.4242561 0 EGADS : 69 Yes 93.4471586 13.4242631 0 EGADS : 70 Yes 93.8409288 32.482011 0 EGADS : 71 Yes 97.8594104 32.482018 0 EGADS : 72 Yes 97.9335611 36.1389817 0 EGADS : 73 Yes 75.3047874 36.1389817 0 EGADS : 74 Yes 93.8409288 32.482011 0 EGADS : 75 Yes 93.4471586 13.4242631 0 EGADS : 76 Yes 168.960236 0 12.9505074 EGADS : 77 Yes 172.609156 0 12.953497 EGADS : 78 Yes 153.930225 0 6.86796425 EGADS : 79 Yes 162.623387 0 6.87508685 EGADS : 80 Yes 154.029174 0 8.17706386 EGADS : 81 Yes 169.00177 0 13.4999966 EGADS : 82 Yes 75.3047874 0 0 EGADS : 83 Yes 97.9335611 0 0 EGADS : 84 Yes 97.8594104 0 0 EGADS : 85 Yes 93.8409288 0 0 EGADS : 86 Yes 93.4471586 0 0 EGADS : 87 Yes 97.4729837 0 0 EGADS : 88 Yes 93.4471586 0 0 EGADS : 89 Yes 93.8409288 0 0 EGADS : 90 Yes 97.1624342 13.7926169 0 EGADS : 91 Yes 93.8265357 13.6735644 0 EGADS : 92 Yes 94.2099771 32.2314198 0 EGADS : 93 Yes 97.6079776 32.3498916 0 EGADS : 94 Yes 100.278023 41.7701593 0 EGADS : 95 Yes 94.7972887 41.7748561 0 EGADS : 96 Yes 107.397556 67.6186586 1.83668579 EGADS : 97 Yes 111.041954 67.6241096 1.25345146 EGADS : 98 Yes 111.257254 68.1412393 1.31307624 EGADS : 99 Yes 107.654637 68.146711 1.88687506 EGADS : 100 Yes 121.207308 95.9421381 4.50820234 EGADS : 101 Yes 122.837313 95.9554542 4.52004059 EGADS : 102 Yes 123.552357 97.6729236 4.7180639 EGADS : 103 Yes 118.391317 97.6729236 3.99272703 EGADS : 104 Yes 121.207308 95.9421381 4.21444802 EGADS : 105 Yes 107.654637 68.146711 0.876544084 EGADS : 106 Yes 107.397556 67.6186586 0.813033541 EGADS : 107 Yes 94.7972887 41.7748561 0 EGADS : 108 Yes 93.9108835 32.2329728 0 EGADS : 109 Yes 93.5781103 13.6748542 0 EGADS : 110 Yes 118.391317 0 3.99272703 EGADS : 111 Yes 123.552357 0 4.7180639 EGADS : 112 Yes 122.837313 0 4.52004059 EGADS : 113 Yes 121.207308 0 4.21444802 EGADS : 114 Yes 107.654637 0 0.876544084 EGADS : 115 Yes 111.257254 0 1.31307624 EGADS : 116 Yes 111.041954 0 1.25345146 EGADS : 117 Yes 107.397556 0 0.813033541 EGADS : 118 Yes 94.7972887 0 0 EGADS : 119 Yes 100.278023 0 0 EGADS : 120 Yes 93.9108835 0 0 EGADS : 121 Yes 97.6079776 0 0 EGADS : 122 Yes 93.5781103 0 0 EGADS : 123 Yes 97.1624342 0 0 EGADS : 124 Yes 93.8265357 0 0 EGADS : 125 Yes 94.2099771 0 0 EGADS : 126 Yes 94.7972887 0 0 EGADS : 127 Yes 107.397556 0 1.83668579 EGADS : 128 Yes 107.654637 0 1.88687506 EGADS : 129 Yes 121.207308 0 4.50820234 EGADS : 130 Yes 100.219054 42.1509694 0 EGADS : 131 Yes 95.2324957 41.963173 0 EGADS : 132 Yes 107.613646 67.3581332 1.77910017 EGADS : 133 Yes 110.892704 67.4707526 0.699981401 EGADS : 134 Yes 111.247925 68.471101 0.828432723 EGADS : 135 Yes 108.034544 68.3613138 1.87771912 EGADS : 136 Yes 121.36809 95.7097324 4.49194275 EGADS : 137 Yes 122.742135 95.7387605 4.2753035 EGADS : 138 Yes 121.327393 95.7291979 4.23513353 EGADS : 139 Yes 107.88707 68.4318513 0.947114671 EGADS : 140 Yes 107.462349 67.4305014 0.82436964 EGADS : 141 Yes 94.9817282 42.0831197 0 EGADS : 142 Yes 121.367879 0 4.23512504 EGADS : 143 Yes 122.701966 0 4.70778241 EGADS : 144 Yes 108.034333 0 0.936789144 EGADS : 145 Yes 111.269456 0 1.85592771 EGADS : 146 Yes 107.462349 0 0.82436964 EGADS : 147 Yes 110.892704 0 0.699981401 EGADS : 148 Yes 94.9817282 0 0 EGADS : 149 Yes 100.219054 0 0 EGADS : 150 Yes 95.2324957 0 0 EGADS : 151 Yes 107.613646 0 1.77910017 EGADS : 152 Yes 107.888388 0 1.86745513 EGADS : 153 Yes 121.327604 0 4.49195125 EGADS : 154 Yes 0 0 1962.43554 EGADS : 155 Yes 0 0 0 EGADS : 156 Yes 0 1953.45847 1962.43554 EGADS : 157 Yes 0 1953.45847 0 EGADS : 158 Yes 2040.09979 0 1962.43554 EGADS : 159 Yes 2040.09979 0 0 EGADS : 160 Yes 2040.09979 1953.45847 1962.43554 EGADS : 161 Yes 2040.09979 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 53.021 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 530.302 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 STD w/BL AFLR4 : 12 CAD geometry 0 STD w/BL AFLR4 : 13 CAD geometry 0 STD w/BL AFLR4 : 14 CAD geometry 0 STD w/BL AFLR4 : 15 CAD geometry 0 STD w/BL AFLR4 : 16 CAD geometry 0 STD w/BL AFLR4 : 17 CAD geometry 0 STD w/BL AFLR4 : 18 CAD geometry 0 STD w/BL AFLR4 : 19 CAD geometry 0 STD w/BL AFLR4 : 20 CAD geometry 0 STD w/BL AFLR4 : 21 CAD geometry 0 STD w/BL AFLR4 : 22 CAD geometry 0 STD w/BL AFLR4 : 23 CAD geometry 0 STD w/BL AFLR4 : 24 CAD geometry 0 STD w/BL AFLR4 : 25 CAD geometry 0 STD w/BL AFLR4 : 26 CAD geometry 0 STD w/BL AFLR4 : 27 CAD geometry 0 STD w/BL AFLR4 : 28 CAD geometry 0 STD w/BL AFLR4 : 29 CAD geometry 0 STD w/BL AFLR4 : 30 CAD geometry 0 STD w/BL AFLR4 : 31 CAD geometry 0 STD w/BL AFLR4 : 32 CAD geometry 0 STD w/BL AFLR4 : 33 CAD geometry 0 STD w/BL AFLR4 : 34 CAD geometry 0 STD w/BL AFLR4 : 35 CAD geometry 0 STD w/BL AFLR4 : 36 CAD geometry 0 STD w/BL AFLR4 : 37 CAD geometry 0 STD w/BL AFLR4 : 38 CAD geometry 0 STD w/BL AFLR4 : 39 CAD geometry 0 STD w/BL AFLR4 : 40 CAD geometry 0 STD w/BL AFLR4 : 41 CAD geometry 0 STD w/BL AFLR4 : 42 CAD geometry 0 STD w/BL AFLR4 : 43 CAD geometry 0 STD w/BL AFLR4 : 44 CAD geometry 0 STD w/BL AFLR4 : 45 CAD geometry 0 STD w/BL AFLR4 : 46 CAD geometry 0 STD w/BL AFLR4 : 47 CAD geometry 0 STD w/BL AFLR4 : 48 CAD geometry 0 STD w/BL AFLR4 : 49 CAD geometry 0 STD w/BL AFLR4 : 50 CAD geometry 0 STD w/BL AFLR4 : 51 CAD geometry 0 STD w/BL AFLR4 : 52 CAD geometry 0 STD w/BL AFLR4 : 53 CAD geometry 0 STD w/BL AFLR4 : 54 CAD geometry 0 STD w/BL AFLR4 : 55 CAD geometry 0 STD w/BL AFLR4 : 56 CAD geometry 0 STD w/BL AFLR4 : 57 CAD geometry 0 STD w/BL AFLR4 : 58 CAD geometry 0 STD w/BL AFLR4 : 59 CAD geometry 0 STD w/BL AFLR4 : 60 CAD geometry 0 STD w/BL AFLR4 : 61 CAD geometry 0 STD w/BL AFLR4 : 62 CAD geometry 0 STD w/BL AFLR4 : 63 CAD geometry 0 STD w/BL AFLR4 : 64 CAD geometry 0 STD w/BL AFLR4 : 65 CAD geometry 0 STD w/BL AFLR4 : 66 CAD geometry 0 STD w/BL AFLR4 : 67 CAD geometry 0 STD w/BL AFLR4 : 68 CAD geometry 0 STD w/BL AFLR4 : 69 CAD geometry 0 STD w/BL AFLR4 : 70 CAD geometry 0 STD w/BL AFLR4 : 71 CAD geometry 0 STD w/BL AFLR4 : 72 CAD geometry 0 STD w/BL AFLR4 : 73 CAD geometry 0 STD w/BL AFLR4 : 74 CAD geometry 0 STD w/BL AFLR4 : 75 CAD geometry 0 STD w/BL AFLR4 : 76 CAD geometry 0 STD w/BL AFLR4 : 77 CAD geometry 0 STD w/BL AFLR4 : 78 CAD geometry 0 STD w/BL AFLR4 : 79 CAD geometry 0 STD w/BL AFLR4 : 80 CAD geometry 0 STD w/BL AFLR4 : 81 CAD geometry 0 STD w/BL AFLR4 : 82 CAD geometry 0 STD w/BL AFLR4 : 83 CAD geometry 0 STD w/BL AFLR4 : 84 CAD geometry 0 STD w/BL AFLR4 : 85 CAD geometry 0 STD w/BL AFLR4 : 86 CAD geometry 0 STD w/BL AFLR4 : 87 CAD geometry 0 STD w/BL AFLR4 : 88 CAD geometry 0 STD w/BL AFLR4 : 89 CAD geometry 0 STD w/BL AFLR4 : 90 CAD geometry 0 STD w/BL AFLR4 : 91 CAD geometry 0 STD w/BL AFLR4 : 92 CAD geometry 0 STD w/BL AFLR4 : 93 CAD geometry 0 STD w/BL AFLR4 : 94 CAD geometry 0 STD w/BL AFLR4 : 95 CAD geometry 0 STD w/BL AFLR4 : 96 CAD geometry 0 STD w/BL AFLR4 : 97 CAD geometry 0 STD w/BL AFLR4 : 98 CAD geometry 0 STD w/BL AFLR4 : 99 CAD geometry 0 STD w/BL AFLR4 : 100 CAD geometry 0 STD w/BL AFLR4 : 101 CAD geometry 0 STD w/BL AFLR4 : 102 CAD geometry 0 STD w/BL AFLR4 : 103 CAD geometry 0 STD w/BL AFLR4 : 104 CAD geometry 0 STD w/BL AFLR4 : 105 CAD geometry 0 STD w/BL AFLR4 : 106 CAD geometry 0 STD w/BL AFLR4 : 107 CAD geometry 0 STD w/BL AFLR4 : 108 CAD geometry 0 STD w/BL AFLR4 : 109 CAD geometry 0 FARFIELD AFLR4 : 110 CAD geometry 0 FARFIELD AFLR4 : 111 CAD geometry 0 FARFIELD AFLR4 : 112 CAD geometry 0 FARFIELD AFLR4 : 113 CAD geometry 0 FARFIELD AFLR4 : 114 CAD geometry 0 FARFIELD AFLR4 : Case has 5 Proximity Checking Components AFLR4 : Component 1 includes Definitions 23 24 28 29 30 31 33 36 40 AFLR4 : Component 2 includes Definitions 37 38 49 50 51 52 53 54 55 56 57 58 AFLR4 : 61 62 63 64 65 66 67 68 69 70 71 72 AFLR4 : 73 74 75 76 77 78 79 80 81 82 83 84 AFLR4 : 85 86 87 88 89 90 91 92 93 94 95 96 AFLR4 : 97 98 99 100 101 102 103 104 105 106 AFLR4 : Component 3 includes Definitions 15 16 17 18 19 20 21 22 25 26 27 34 AFLR4 : 35 42 43 44 45 46 47 48 59 60 AFLR4 : Component 4 includes Definitions 9 10 11 12 13 14 32 39 41 107 108 AFLR4 : Component 5 includes Definitions 1 2 3 4 5 6 7 8 AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Define CAD surface definition 17 AFLR4 : Define CAD surface definition 18 AFLR4 : Define CAD surface definition 19 AFLR4 : Define CAD surface definition 20 AFLR4 : Define CAD surface definition 21 AFLR4 : Define CAD surface definition 22 AFLR4 : Define CAD surface definition 23 AFLR4 : Define CAD surface definition 24 AFLR4 : Define CAD surface definition 25 AFLR4 : Define CAD surface definition 26 AFLR4 : Define CAD surface definition 27 AFLR4 : Define CAD surface definition 28 AFLR4 : Define CAD surface definition 29 AFLR4 : Define CAD surface definition 30 AFLR4 : Define CAD surface definition 31 AFLR4 : Define CAD surface definition 32 AFLR4 : Define CAD surface definition 33 AFLR4 : Define CAD surface definition 34 AFLR4 : Define CAD surface definition 35 AFLR4 : Define CAD surface definition 36 AFLR4 : Define CAD surface definition 37 AFLR4 : Define CAD surface definition 38 AFLR4 : Define CAD surface definition 39 AFLR4 : Define CAD surface definition 40 AFLR4 : Define CAD surface definition 41 AFLR4 : Define CAD surface definition 42 AFLR4 : Define CAD surface definition 43 AFLR4 : Define CAD surface definition 44 AFLR4 : Define CAD surface definition 45 AFLR4 : Define CAD surface definition 46 AFLR4 : Define CAD surface definition 47 AFLR4 : Define CAD surface definition 48 AFLR4 : Define CAD surface definition 49 AFLR4 : Define CAD surface definition 50 AFLR4 : Define CAD surface definition 51 AFLR4 : Define CAD surface definition 52 AFLR4 : Define CAD surface definition 53 AFLR4 : Define CAD surface definition 54 AFLR4 : Define CAD surface definition 55 AFLR4 : Define CAD surface definition 56 AFLR4 : Define CAD surface definition 57 AFLR4 : Define CAD surface definition 58 AFLR4 : Define CAD surface definition 59 AFLR4 : Define CAD surface definition 60 AFLR4 : Define CAD surface definition 61 AFLR4 : Define CAD surface definition 62 AFLR4 : Define CAD surface definition 63 AFLR4 : Define CAD surface definition 64 AFLR4 : Define CAD surface definition 65 AFLR4 : Define CAD surface definition 66 AFLR4 : Define CAD surface definition 67 AFLR4 : Define CAD surface definition 68 AFLR4 : Define CAD surface definition 69 AFLR4 : Define CAD surface definition 70 AFLR4 : Define CAD surface definition 71 AFLR4 : Define CAD surface definition 72 AFLR4 : Define CAD surface definition 73 AFLR4 : Define CAD surface definition 74 AFLR4 : Define CAD surface definition 75 AFLR4 : Define CAD surface definition 76 AFLR4 : Define CAD surface definition 77 AFLR4 : Define CAD surface definition 78 AFLR4 : Define CAD surface definition 79 AFLR4 : Define CAD surface definition 80 AFLR4 : Define CAD surface definition 81 AFLR4 : Define CAD surface definition 82 AFLR4 : Define CAD surface definition 83 AFLR4 : Define CAD surface definition 84 AFLR4 : Define CAD surface definition 85 AFLR4 : Define CAD surface definition 86 AFLR4 : Define CAD surface definition 87 AFLR4 : Define CAD surface definition 88 AFLR4 : Define CAD surface definition 89 AFLR4 : Define CAD surface definition 90 AFLR4 : Define CAD surface definition 91 AFLR4 : Define CAD surface definition 92 AFLR4 : Define CAD surface definition 93 AFLR4 : Define CAD surface definition 94 AFLR4 : Define CAD surface definition 95 AFLR4 : Define CAD surface definition 96 AFLR4 : Define CAD surface definition 97 AFLR4 : Define CAD surface definition 98 AFLR4 : Define CAD surface definition 99 AFLR4 : Define CAD surface definition 100 AFLR4 : Define CAD surface definition 101 AFLR4 : Define CAD surface definition 102 AFLR4 : Define CAD surface definition 103 AFLR4 : Define CAD surface definition 104 AFLR4 : Define CAD surface definition 105 AFLR4 : Define CAD surface definition 106 AFLR4 : Define CAD surface definition 107 AFLR4 : Define CAD surface definition 108 AFLR4 : Define CAD surface definition 109 AFLR4 : Define CAD surface definition 110 AFLR4 : Define CAD surface definition 111 AFLR4 : Define CAD surface definition 112 AFLR4 : Define CAD surface definition 113 AFLR4 : Define CAD surface definition 114 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 339 605 0 AFLR4 : Nodes, Trias,Quads= 362 651 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 319 563 0 AFLR4 : Nodes, Trias,Quads= 284 493 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 340 607 0 AFLR4 : Nodes, Trias,Quads= 362 651 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 321 567 0 AFLR4 : Nodes, Trias,Quads= 284 493 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 340 607 0 AFLR4 : Nodes, Trias,Quads= 362 651 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 321 567 0 AFLR4 : Nodes, Trias,Quads= 284 493 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 339 605 0 AFLR4 : Nodes, Trias,Quads= 362 651 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 319 563 0 AFLR4 : Nodes, Trias,Quads= 284 493 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 15 19 0 AFLR4 : Nodes, Trias,Quads= 9 7 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 15 19 0 AFLR4 : Nodes, Trias,Quads= 9 7 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 47 65 0 AFLR4 : Nodes, Trias,Quads= 27 25 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 24 31 0 AFLR4 : Nodes, Trias,Quads= 23 29 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 24 31 0 AFLR4 : Nodes, Trias,Quads= 22 27 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 47 65 0 AFLR4 : Nodes, Trias,Quads= 27 25 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 51 67 0 AFLR4 : Nodes, Trias,Quads= 58 81 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 1615 3003 0 AFLR4 : Nodes, Trias,Quads= 1188 2149 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 90 127 0 AFLR4 : Nodes, Trias,Quads= 51 49 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 216 367 0 AFLR4 : Nodes, Trias,Quads= 174 283 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 51 67 0 AFLR4 : Nodes, Trias,Quads= 51 67 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 1677 3126 0 AFLR4 : Nodes, Trias,Quads= 1210 2192 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 35 44 0 AFLR4 : Nodes, Trias,Quads= 24 22 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 11 13 0 AFLR4 : Nodes, Trias,Quads= 9 9 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 907 1650 0 AFLR4 : Nodes, Trias,Quads= 569 974 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 3270 6232 0 AFLR4 : Nodes, Trias,Quads= 1907 3506 0 AFLR4 : Generate optimal mesh on surface definition 25 AFLR2 : Nodes, Trias,Quads= 220 375 0 AFLR4 : Nodes, Trias,Quads= 176 287 0 AFLR4 : Generate optimal mesh on surface definition 26 AFLR2 : Nodes, Trias,Quads= 80 108 0 AFLR4 : Nodes, Trias,Quads= 50 48 0 AFLR4 : Generate optimal mesh on surface definition 27 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Generate optimal mesh on surface definition 28 AFLR2 : Nodes, Trias,Quads= 902 1640 0 AFLR4 : Nodes, Trias,Quads= 561 958 0 AFLR4 : Generate optimal mesh on surface definition 29 AFLR2 : Nodes, Trias,Quads= 106 170 0 AFLR4 : Nodes, Trias,Quads= 106 170 0 AFLR4 : Generate optimal mesh on surface definition 30 AFLR2 : Nodes, Trias,Quads= 1586 2835 0 AFLR4 : Nodes, Trias,Quads= 1651 2965 0 AFLR4 : Generate optimal mesh on surface definition 31 AFLR2 : Nodes, Trias,Quads= 3418 6528 0 AFLR4 : Nodes, Trias,Quads= 1888 3468 0 AFLR4 : Generate optimal mesh on surface definition 32 AFLR2 : Nodes, Trias,Quads= 1868 3486 0 AFLR4 : Nodes, Trias,Quads= 1347 2444 0 AFLR4 : Generate optimal mesh on surface definition 33 AFLR2 : Nodes, Trias,Quads= 1025 1836 0 AFLR4 : Nodes, Trias,Quads= 1213 2212 0 AFLR4 : Generate optimal mesh on surface definition 34 AFLR2 : Nodes, Trias,Quads= 1436 2654 0 AFLR4 : Nodes, Trias,Quads= 979 1740 0 AFLR4 : Generate optimal mesh on surface definition 35 AFLR2 : Nodes, Trias,Quads= 1684 3140 0 AFLR4 : Nodes, Trias,Quads= 1216 2204 0 AFLR4 : Generate optimal mesh on surface definition 36 AFLR2 : Nodes, Trias,Quads= 1579 2821 0 AFLR4 : Nodes, Trias,Quads= 1648 2959 0 AFLR4 : Generate optimal mesh on surface definition 37 AFLR2 : Nodes, Trias,Quads= 2154 4060 0 AFLR4 : Nodes, Trias,Quads= 2140 4032 0 AFLR4 : Generate optimal mesh on surface definition 38 AFLR2 : Nodes, Trias,Quads= 2585 4915 0 AFLR4 : Nodes, Trias,Quads= 2189 4123 0 AFLR4 : Generate optimal mesh on surface definition 39 AFLR2 : Nodes, Trias,Quads= 1916 3582 0 AFLR4 : Nodes, Trias,Quads= 1367 2484 0 AFLR4 : Generate optimal mesh on surface definition 40 AFLR2 : Nodes, Trias,Quads= 1026 1838 0 AFLR4 : Nodes, Trias,Quads= 1215 2216 0 AFLR4 : Generate optimal mesh on surface definition 41 AFLR2 : Nodes, Trias,Quads= 47 60 0 AFLR4 : Nodes, Trias,Quads= 32 30 0 AFLR4 : Generate optimal mesh on surface definition 42 AFLR2 : Nodes, Trias,Quads= 35 44 0 AFLR4 : Nodes, Trias,Quads= 24 22 0 AFLR4 : Generate optimal mesh on surface definition 43 AFLR2 : Nodes, Trias,Quads= 11 13 0 AFLR4 : Nodes, Trias,Quads= 9 9 0 AFLR4 : Generate optimal mesh on surface definition 44 AFLR2 : Nodes, Trias,Quads= 59 84 0 AFLR4 : Nodes, Trias,Quads= 32 30 0 AFLR4 : Generate optimal mesh on surface definition 45 AFLR2 : Nodes, Trias,Quads= 41 53 0 AFLR4 : Nodes, Trias,Quads= 48 67 0 AFLR4 : Generate optimal mesh on surface definition 46 AFLR2 : Nodes, Trias,Quads= 51 67 0 AFLR4 : Nodes, Trias,Quads= 50 65 0 AFLR4 : Generate optimal mesh on surface definition 47 AFLR2 : Nodes, Trias,Quads= 80 108 0 AFLR4 : Nodes, Trias,Quads= 50 48 0 AFLR4 : Generate optimal mesh on surface definition 48 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Generate optimal mesh on surface definition 49 AFLR2 : Nodes, Trias,Quads= 2582 4909 0 AFLR4 : Nodes, Trias,Quads= 2199 4143 0 AFLR4 : Generate optimal mesh on surface definition 50 AFLR2 : Nodes, Trias,Quads= 2158 4068 0 AFLR4 : Nodes, Trias,Quads= 2139 4030 0 AFLR4 : Generate optimal mesh on surface definition 51 AFLR2 : Nodes, Trias,Quads= 46 65 0 AFLR4 : Nodes, Trias,Quads= 39 51 0 AFLR4 : Generate optimal mesh on surface definition 52 AFLR2 : Nodes, Trias,Quads= 108 144 0 AFLR4 : Nodes, Trias,Quads= 102 132 0 AFLR4 : Generate optimal mesh on surface definition 53 AFLR2 : Nodes, Trias,Quads= 46 65 0 AFLR4 : Nodes, Trias,Quads= 39 51 0 AFLR4 : Generate optimal mesh on surface definition 54 AFLR2 : Nodes, Trias,Quads= 3787 7224 0 AFLR4 : Nodes, Trias,Quads= 2368 4386 0 AFLR4 : Generate optimal mesh on surface definition 55 AFLR2 : Nodes, Trias,Quads= 3490 6642 0 AFLR4 : Nodes, Trias,Quads= 2094 3850 0 AFLR4 : Generate optimal mesh on surface definition 56 AFLR2 : Nodes, Trias,Quads= 74 114 0 AFLR4 : Nodes, Trias,Quads= 49 64 0 AFLR4 : Generate optimal mesh on surface definition 57 AFLR2 : Nodes, Trias,Quads= 148 206 0 AFLR4 : Nodes, Trias,Quads= 111 132 0 AFLR4 : Generate optimal mesh on surface definition 58 AFLR2 : Nodes, Trias,Quads= 70 107 0 AFLR4 : Nodes, Trias,Quads= 49 65 0 AFLR4 : Generate optimal mesh on surface definition 59 AFLR2 : Nodes, Trias,Quads= 130 209 0 AFLR4 : Nodes, Trias,Quads= 94 137 0 AFLR4 : Generate optimal mesh on surface definition 60 AFLR2 : Nodes, Trias,Quads= 215 365 0 AFLR4 : Nodes, Trias,Quads= 176 287 0 AFLR4 : Generate optimal mesh on surface definition 61 AFLR2 : Nodes, Trias,Quads= 3535 6727 0 AFLR4 : Nodes, Trias,Quads= 2180 4017 0 AFLR4 : Generate optimal mesh on surface definition 62 AFLR2 : Nodes, Trias,Quads= 74 114 0 AFLR4 : Nodes, Trias,Quads= 48 62 0 AFLR4 : Generate optimal mesh on surface definition 63 AFLR2 : Nodes, Trias,Quads= 148 206 0 AFLR4 : Nodes, Trias,Quads= 111 132 0 AFLR4 : Generate optimal mesh on surface definition 64 AFLR2 : Nodes, Trias,Quads= 70 107 0 AFLR4 : Nodes, Trias,Quads= 49 65 0 AFLR4 : Generate optimal mesh on surface definition 65 AFLR2 : Nodes, Trias,Quads= 46 65 0 AFLR4 : Nodes, Trias,Quads= 39 51 0 AFLR4 : Generate optimal mesh on surface definition 66 AFLR2 : Nodes, Trias,Quads= 108 144 0 AFLR4 : Nodes, Trias,Quads= 94 116 0 AFLR4 : Generate optimal mesh on surface definition 67 AFLR2 : Nodes, Trias,Quads= 46 65 0 AFLR4 : Nodes, Trias,Quads= 39 51 0 AFLR4 : Generate optimal mesh on surface definition 68 AFLR2 : Nodes, Trias,Quads= 3573 6801 0 AFLR4 : Nodes, Trias,Quads= 2281 4217 0 AFLR4 : Generate optimal mesh on surface definition 69 AFLR2 : Nodes, Trias,Quads= 245 414 0 AFLR4 : Nodes, Trias,Quads= 224 372 0 AFLR4 : Generate optimal mesh on surface definition 70 AFLR2 : Nodes, Trias,Quads= 50 67 0 AFLR4 : Nodes, Trias,Quads= 51 69 0 AFLR4 : Generate optimal mesh on surface definition 71 AFLR2 : Nodes, Trias,Quads= 114 155 0 AFLR4 : Nodes, Trias,Quads= 78 83 0 AFLR4 : Generate optimal mesh on surface definition 72 AFLR2 : Nodes, Trias,Quads= 28 36 0 AFLR4 : Nodes, Trias,Quads= 31 42 0 AFLR4 : Generate optimal mesh on surface definition 73 AFLR2 : Nodes, Trias,Quads= 39 50 0 AFLR4 : Nodes, Trias,Quads= 42 56 0 AFLR4 : Generate optimal mesh on surface definition 74 AFLR2 : Nodes, Trias,Quads= 157 216 0 AFLR4 : Nodes, Trias,Quads= 141 184 0 AFLR4 : Generate optimal mesh on surface definition 75 AFLR2 : Nodes, Trias,Quads= 31 39 0 AFLR4 : Nodes, Trias,Quads= 32 41 0 AFLR4 : Generate optimal mesh on surface definition 76 AFLR2 : Nodes, Trias,Quads= 36 49 0 AFLR4 : Nodes, Trias,Quads= 21 19 0 AFLR4 : Generate optimal mesh on surface definition 77 AFLR2 : Nodes, Trias,Quads= 32 40 0 AFLR4 : Nodes, Trias,Quads= 34 44 0 AFLR4 : Generate optimal mesh on surface definition 78 AFLR2 : Nodes, Trias,Quads= 148 208 0 AFLR4 : Nodes, Trias,Quads= 86 84 0 AFLR4 : Generate optimal mesh on surface definition 79 AFLR2 : Nodes, Trias,Quads= 31 40 0 AFLR4 : Nodes, Trias,Quads= 33 44 0 AFLR4 : Generate optimal mesh on surface definition 80 AFLR2 : Nodes, Trias,Quads= 28 36 0 AFLR4 : Nodes, Trias,Quads= 30 40 0 AFLR4 : Generate optimal mesh on surface definition 81 AFLR2 : Nodes, Trias,Quads= 111 158 0 AFLR4 : Nodes, Trias,Quads= 65 66 0 AFLR4 : Generate optimal mesh on surface definition 82 AFLR2 : Nodes, Trias,Quads= 33 41 0 AFLR4 : Nodes, Trias,Quads= 40 55 0 AFLR4 : Generate optimal mesh on surface definition 83 AFLR2 : Nodes, Trias,Quads= 328 564 0 AFLR4 : Nodes, Trias,Quads= 305 518 0 AFLR4 : Generate optimal mesh on surface definition 84 AFLR2 : Nodes, Trias,Quads= 36 49 0 AFLR4 : Nodes, Trias,Quads= 21 19 0 AFLR4 : Generate optimal mesh on surface definition 85 AFLR2 : Nodes, Trias,Quads= 32 41 0 AFLR4 : Nodes, Trias,Quads= 34 45 0 AFLR4 : Generate optimal mesh on surface definition 86 AFLR2 : Nodes, Trias,Quads= 157 216 0 AFLR4 : Nodes, Trias,Quads= 119 140 0 AFLR4 : Generate optimal mesh on surface definition 87 AFLR2 : Nodes, Trias,Quads= 39 51 0 AFLR4 : Nodes, Trias,Quads= 43 59 0 AFLR4 : Generate optimal mesh on surface definition 88 AFLR2 : Nodes, Trias,Quads= 28 36 0 AFLR4 : Nodes, Trias,Quads= 30 40 0 AFLR4 : Generate optimal mesh on surface definition 89 AFLR2 : Nodes, Trias,Quads= 111 158 0 AFLR4 : Nodes, Trias,Quads= 65 66 0 AFLR4 : Generate optimal mesh on surface definition 90 AFLR2 : Nodes, Trias,Quads= 33 41 0 AFLR4 : Nodes, Trias,Quads= 40 55 0 AFLR4 : Generate optimal mesh on surface definition 91 AFLR2 : Nodes, Trias,Quads= 329 566 0 AFLR4 : Nodes, Trias,Quads= 305 518 0 AFLR4 : Generate optimal mesh on surface definition 92 AFLR2 : Nodes, Trias,Quads= 245 414 0 AFLR4 : Nodes, Trias,Quads= 225 374 0 AFLR4 : Generate optimal mesh on surface definition 93 AFLR2 : Nodes, Trias,Quads= 50 67 0 AFLR4 : Nodes, Trias,Quads= 51 69 0 AFLR4 : Generate optimal mesh on surface definition 94 AFLR2 : Nodes, Trias,Quads= 114 155 0 AFLR4 : Nodes, Trias,Quads= 78 83 0 AFLR4 : Generate optimal mesh on surface definition 95 AFLR2 : Nodes, Trias,Quads= 28 36 0 AFLR4 : Nodes, Trias,Quads= 31 42 0 AFLR4 : Generate optimal mesh on surface definition 96 AFLR2 : Nodes, Trias,Quads= 32 41 0 AFLR4 : Nodes, Trias,Quads= 35 47 0 AFLR4 : Generate optimal mesh on surface definition 97 AFLR2 : Nodes, Trias,Quads= 148 208 0 AFLR4 : Nodes, Trias,Quads= 112 136 0 AFLR4 : Generate optimal mesh on surface definition 98 AFLR2 : Nodes, Trias,Quads= 33 42 0 AFLR4 : Nodes, Trias,Quads= 34 44 0 AFLR4 : Generate optimal mesh on surface definition 99 AFLR2 : Nodes, Trias,Quads= 251 422 0 AFLR4 : Nodes, Trias,Quads= 208 336 0 AFLR4 : Generate optimal mesh on surface definition 100 AFLR2 : Nodes, Trias,Quads= 332 556 0 AFLR4 : Nodes, Trias,Quads= 250 392 0 AFLR4 : Generate optimal mesh on surface definition 101 AFLR2 : Nodes, Trias,Quads= 295 490 0 AFLR4 : Nodes, Trias,Quads= 216 332 0 AFLR4 : Generate optimal mesh on surface definition 102 AFLR2 : Nodes, Trias,Quads= 207 341 0 AFLR4 : Nodes, Trias,Quads= 174 275 0 AFLR4 : Generate optimal mesh on surface definition 103 AFLR2 : Nodes, Trias,Quads= 327 547 0 AFLR4 : Nodes, Trias,Quads= 240 373 0 AFLR4 : Generate optimal mesh on surface definition 104 AFLR2 : Nodes, Trias,Quads= 208 343 0 AFLR4 : Nodes, Trias,Quads= 173 273 0 AFLR4 : Generate optimal mesh on surface definition 105 AFLR2 : Nodes, Trias,Quads= 248 416 0 AFLR4 : Nodes, Trias,Quads= 208 336 0 AFLR4 : Generate optimal mesh on surface definition 106 AFLR2 : Nodes, Trias,Quads= 297 493 0 AFLR4 : Nodes, Trias,Quads= 225 349 0 AFLR4 : Generate optimal mesh on surface definition 107 AFLR2 : Nodes, Trias,Quads= 40 57 0 AFLR4 : Nodes, Trias,Quads= 30 37 0 AFLR4 : Generate optimal mesh on surface definition 108 AFLR2 : Nodes, Trias,Quads= 40 57 0 AFLR4 : Nodes, Trias,Quads= 31 39 0 AFLR4 : Generate optimal mesh on surface definition 109 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 110 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 111 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 112 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 113 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 114 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 39758 79508 9980 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 39758 79508 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 397 713 0 AFLR4 : Nodes, Trias,Quads= 416 751 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 387 691 0 AFLR4 : Nodes, Trias,Quads= 346 609 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 396 711 0 AFLR4 : Nodes, Trias,Quads= 417 753 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 388 693 0 AFLR4 : Nodes, Trias,Quads= 344 605 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 395 709 0 AFLR4 : Nodes, Trias,Quads= 416 751 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 388 693 0 AFLR4 : Nodes, Trias,Quads= 344 605 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 395 709 0 AFLR4 : Nodes, Trias,Quads= 416 751 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 387 691 0 AFLR4 : Nodes, Trias,Quads= 346 609 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 18 23 0 AFLR4 : Nodes, Trias,Quads= 11 9 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 18 23 0 AFLR4 : Nodes, Trias,Quads= 11 9 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 56 77 0 AFLR4 : Nodes, Trias,Quads= 33 31 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 28 37 0 AFLR4 : Nodes, Trias,Quads= 25 31 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 29 38 0 AFLR4 : Nodes, Trias,Quads= 28 36 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 56 77 0 AFLR4 : Nodes, Trias,Quads= 33 31 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 60 80 0 AFLR4 : Nodes, Trias,Quads= 59 78 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 1730 3226 0 AFLR4 : Nodes, Trias,Quads= 1387 2540 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 100 140 0 AFLR4 : Nodes, Trias,Quads= 58 56 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 271 470 0 AFLR4 : Nodes, Trias,Quads= 208 344 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 57 75 0 AFLR4 : Nodes, Trias,Quads= 61 83 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 1821 3408 0 AFLR4 : Nodes, Trias,Quads= 1413 2592 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 38 49 0 AFLR4 : Nodes, Trias,Quads= 25 23 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 15 19 0 AFLR4 : Nodes, Trias,Quads= 15 19 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 1020 1868 0 AFLR4 : Nodes, Trias,Quads= 1567 2962 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 3285 6257 0 AFLR4 : Nodes, Trias,Quads= 2653 4993 0 AFLR4 : Generate optimal mesh on surface definition 25 AFLR2 : Nodes, Trias,Quads= 268 463 0 AFLR4 : Nodes, Trias,Quads= 211 349 0 AFLR4 : Generate optimal mesh on surface definition 26 AFLR2 : Nodes, Trias,Quads= 96 133 0 AFLR4 : Nodes, Trias,Quads= 57 55 0 AFLR4 : Generate optimal mesh on surface definition 27 AFLR2 : Nodes, Trias,Quads= 15 18 0 AFLR4 : Nodes, Trias,Quads= 15 18 0 AFLR4 : Generate optimal mesh on surface definition 28 AFLR2 : Nodes, Trias,Quads= 1004 1837 0 AFLR4 : Nodes, Trias,Quads= 1550 2929 0 AFLR4 : Generate optimal mesh on surface definition 29 AFLR2 : Nodes, Trias,Quads= 106 170 0 AFLR4 : Nodes, Trias,Quads= 116 190 0 AFLR4 : Generate optimal mesh on surface definition 30 AFLR2 : Nodes, Trias,Quads= 1641 2940 0 AFLR4 : Nodes, Trias,Quads= 3186 6030 0 AFLR4 : Generate optimal mesh on surface definition 31 AFLR2 : Nodes, Trias,Quads= 3518 6723 0 AFLR4 : Nodes, Trias,Quads= 2633 4953 0 AFLR4 : Generate optimal mesh on surface definition 32 AFLR2 : Nodes, Trias,Quads= 2078 3899 0 AFLR4 : Nodes, Trias,Quads= 1693 3129 0 AFLR4 : Generate optimal mesh on surface definition 33 AFLR2 : Nodes, Trias,Quads= 1088 1956 0 AFLR4 : Nodes, Trias,Quads= 2728 5236 0 AFLR4 : Generate optimal mesh on surface definition 34 AFLR2 : Nodes, Trias,Quads= 1551 2878 0 AFLR4 : Nodes, Trias,Quads= 1231 2238 0 AFLR4 : Generate optimal mesh on surface definition 35 AFLR2 : Nodes, Trias,Quads= 1791 3350 0 AFLR4 : Nodes, Trias,Quads= 1415 2598 0 AFLR4 : Generate optimal mesh on surface definition 36 AFLR2 : Nodes, Trias,Quads= 1642 2942 0 AFLR4 : Nodes, Trias,Quads= 3182 6022 0 AFLR4 : Generate optimal mesh on surface definition 37 AFLR2 : Nodes, Trias,Quads= 2194 4132 0 AFLR4 : Nodes, Trias,Quads= 2357 4458 0 AFLR4 : Generate optimal mesh on surface definition 38 AFLR2 : Nodes, Trias,Quads= 3014 5761 0 AFLR4 : Nodes, Trias,Quads= 2581 4895 0 AFLR4 : Generate optimal mesh on surface definition 39 AFLR2 : Nodes, Trias,Quads= 2124 3993 0 AFLR4 : Nodes, Trias,Quads= 1733 3211 0 AFLR4 : Generate optimal mesh on surface definition 40 AFLR2 : Nodes, Trias,Quads= 1089 1958 0 AFLR4 : Nodes, Trias,Quads= 2719 5218 0 AFLR4 : Generate optimal mesh on surface definition 41 AFLR2 : Nodes, Trias,Quads= 60 81 0 AFLR4 : Nodes, Trias,Quads= 37 35 0 AFLR4 : Generate optimal mesh on surface definition 42 AFLR2 : Nodes, Trias,Quads= 37 47 0 AFLR4 : Nodes, Trias,Quads= 25 23 0 AFLR4 : Generate optimal mesh on surface definition 43 AFLR2 : Nodes, Trias,Quads= 15 18 0 AFLR4 : Nodes, Trias,Quads= 16 20 0 AFLR4 : Generate optimal mesh on surface definition 44 AFLR2 : Nodes, Trias,Quads= 71 100 0 AFLR4 : Nodes, Trias,Quads= 40 38 0 AFLR4 : Generate optimal mesh on surface definition 45 AFLR2 : Nodes, Trias,Quads= 48 63 0 AFLR4 : Nodes, Trias,Quads= 51 69 0 AFLR4 : Generate optimal mesh on surface definition 46 AFLR2 : Nodes, Trias,Quads= 57 75 0 AFLR4 : Nodes, Trias,Quads= 62 85 0 AFLR4 : Generate optimal mesh on surface definition 47 AFLR2 : Nodes, Trias,Quads= 85 111 0 AFLR4 : Nodes, Trias,Quads= 57 55 0 AFLR4 : Generate optimal mesh on surface definition 48 AFLR2 : Nodes, Trias,Quads= 15 18 0 AFLR4 : Nodes, Trias,Quads= 15 18 0 AFLR4 : Generate optimal mesh on surface definition 49 AFLR2 : Nodes, Trias,Quads= 3046 5824 0 AFLR4 : Nodes, Trias,Quads= 2604 4940 0 AFLR4 : Generate optimal mesh on surface definition 50 AFLR2 : Nodes, Trias,Quads= 2207 4159 0 AFLR4 : Nodes, Trias,Quads= 2346 4437 0 AFLR4 : Generate optimal mesh on surface definition 51 AFLR2 : Nodes, Trias,Quads= 53 77 0 AFLR4 : Nodes, Trias,Quads= 41 53 0 AFLR4 : Generate optimal mesh on surface definition 52 AFLR2 : Nodes, Trias,Quads= 121 160 0 AFLR4 : Nodes, Trias,Quads= 99 116 0 AFLR4 : Generate optimal mesh on surface definition 53 AFLR2 : Nodes, Trias,Quads= 55 80 0 AFLR4 : Nodes, Trias,Quads= 44 58 0 AFLR4 : Generate optimal mesh on surface definition 54 AFLR2 : Nodes, Trias,Quads= 4380 8388 0 AFLR4 : Nodes, Trias,Quads= 2756 5140 0 AFLR4 : Generate optimal mesh on surface definition 55 AFLR2 : Nodes, Trias,Quads= 3996 7635 0 AFLR4 : Nodes, Trias,Quads= 2397 4437 0 AFLR4 : Generate optimal mesh on surface definition 56 AFLR2 : Nodes, Trias,Quads= 78 120 0 AFLR4 : Nodes, Trias,Quads= 51 66 0 AFLR4 : Generate optimal mesh on surface definition 57 AFLR2 : Nodes, Trias,Quads= 164 223 0 AFLR4 : Nodes, Trias,Quads= 162 219 0 AFLR4 : Generate optimal mesh on surface definition 58 AFLR2 : Nodes, Trias,Quads= 73 112 0 AFLR4 : Nodes, Trias,Quads= 48 62 0 AFLR4 : Generate optimal mesh on surface definition 59 AFLR2 : Nodes, Trias,Quads= 175 291 0 AFLR4 : Nodes, Trias,Quads= 161 263 0 AFLR4 : Generate optimal mesh on surface definition 60 AFLR2 : Nodes, Trias,Quads= 260 448 0 AFLR4 : Nodes, Trias,Quads= 208 344 0 AFLR4 : Generate optimal mesh on surface definition 61 AFLR2 : Nodes, Trias,Quads= 4125 7885 0 AFLR4 : Nodes, Trias,Quads= 2505 4645 0 AFLR4 : Generate optimal mesh on surface definition 62 AFLR2 : Nodes, Trias,Quads= 78 120 0 AFLR4 : Nodes, Trias,Quads= 51 66 0 AFLR4 : Generate optimal mesh on surface definition 63 AFLR2 : Nodes, Trias,Quads= 175 244 0 AFLR4 : Nodes, Trias,Quads= 163 220 0 AFLR4 : Generate optimal mesh on surface definition 64 AFLR2 : Nodes, Trias,Quads= 73 112 0 AFLR4 : Nodes, Trias,Quads= 48 62 0 AFLR4 : Generate optimal mesh on surface definition 65 AFLR2 : Nodes, Trias,Quads= 53 77 0 AFLR4 : Nodes, Trias,Quads= 41 53 0 AFLR4 : Generate optimal mesh on surface definition 66 AFLR2 : Nodes, Trias,Quads= 124 169 0 AFLR4 : Nodes, Trias,Quads= 111 143 0 AFLR4 : Generate optimal mesh on surface definition 67 AFLR2 : Nodes, Trias,Quads= 56 82 0 AFLR4 : Nodes, Trias,Quads= 43 56 0 AFLR4 : Generate optimal mesh on surface definition 68 AFLR2 : Nodes, Trias,Quads= 4113 7862 0 AFLR4 : Nodes, Trias,Quads= 2649 4934 0 AFLR4 : Generate optimal mesh on surface definition 69 AFLR2 : Nodes, Trias,Quads= 300 515 0 AFLR4 : Nodes, Trias,Quads= 283 481 0 AFLR4 : Generate optimal mesh on surface definition 70 AFLR2 : Nodes, Trias,Quads= 57 78 0 AFLR4 : Nodes, Trias,Quads= 55 74 0 AFLR4 : Generate optimal mesh on surface definition 71 AFLR2 : Nodes, Trias,Quads= 135 188 0 AFLR4 : Nodes, Trias,Quads= 87 92 0 AFLR4 : Generate optimal mesh on surface definition 72 AFLR2 : Nodes, Trias,Quads= 33 42 0 AFLR4 : Nodes, Trias,Quads= 36 48 0 AFLR4 : Generate optimal mesh on surface definition 73 AFLR2 : Nodes, Trias,Quads= 43 55 0 AFLR4 : Nodes, Trias,Quads= 44 57 0 AFLR4 : Generate optimal mesh on surface definition 74 AFLR2 : Nodes, Trias,Quads= 186 257 0 AFLR4 : Nodes, Trias,Quads= 180 245 0 AFLR4 : Generate optimal mesh on surface definition 75 AFLR2 : Nodes, Trias,Quads= 31 39 0 AFLR4 : Nodes, Trias,Quads= 31 39 0 AFLR4 : Generate optimal mesh on surface definition 76 AFLR2 : Nodes, Trias,Quads= 39 53 0 AFLR4 : Nodes, Trias,Quads= 23 21 0 AFLR4 : Generate optimal mesh on surface definition 77 AFLR2 : Nodes, Trias,Quads= 32 40 0 AFLR4 : Nodes, Trias,Quads= 32 40 0 AFLR4 : Generate optimal mesh on surface definition 78 AFLR2 : Nodes, Trias,Quads= 169 238 0 AFLR4 : Nodes, Trias,Quads= 101 102 0 AFLR4 : Generate optimal mesh on surface definition 79 AFLR2 : Nodes, Trias,Quads= 34 44 0 AFLR4 : Nodes, Trias,Quads= 36 48 0 AFLR4 : Generate optimal mesh on surface definition 80 AFLR2 : Nodes, Trias,Quads= 33 43 0 AFLR4 : Nodes, Trias,Quads= 36 49 0 AFLR4 : Generate optimal mesh on surface definition 81 AFLR2 : Nodes, Trias,Quads= 132 188 0 AFLR4 : Nodes, Trias,Quads= 79 82 0 AFLR4 : Generate optimal mesh on surface definition 82 AFLR2 : Nodes, Trias,Quads= 40 51 0 AFLR4 : Nodes, Trias,Quads= 46 63 0 AFLR4 : Generate optimal mesh on surface definition 83 AFLR2 : Nodes, Trias,Quads= 402 701 0 AFLR4 : Nodes, Trias,Quads= 405 707 0 AFLR4 : Generate optimal mesh on surface definition 84 AFLR2 : Nodes, Trias,Quads= 39 53 0 AFLR4 : Nodes, Trias,Quads= 23 21 0 AFLR4 : Generate optimal mesh on surface definition 85 AFLR2 : Nodes, Trias,Quads= 32 41 0 AFLR4 : Nodes, Trias,Quads= 31 39 0 AFLR4 : Generate optimal mesh on surface definition 86 AFLR2 : Nodes, Trias,Quads= 186 260 0 AFLR4 : Nodes, Trias,Quads= 140 168 0 AFLR4 : Generate optimal mesh on surface definition 87 AFLR2 : Nodes, Trias,Quads= 42 54 0 AFLR4 : Nodes, Trias,Quads= 48 66 0 AFLR4 : Generate optimal mesh on surface definition 88 AFLR2 : Nodes, Trias,Quads= 34 44 0 AFLR4 : Nodes, Trias,Quads= 37 50 0 AFLR4 : Generate optimal mesh on surface definition 89 AFLR2 : Nodes, Trias,Quads= 132 188 0 AFLR4 : Nodes, Trias,Quads= 79 82 0 AFLR4 : Generate optimal mesh on surface definition 90 AFLR2 : Nodes, Trias,Quads= 40 51 0 AFLR4 : Nodes, Trias,Quads= 45 61 0 AFLR4 : Generate optimal mesh on surface definition 91 AFLR2 : Nodes, Trias,Quads= 401 699 0 AFLR4 : Nodes, Trias,Quads= 404 705 0 AFLR4 : Generate optimal mesh on surface definition 92 AFLR2 : Nodes, Trias,Quads= 293 502 0 AFLR4 : Nodes, Trias,Quads= 277 470 0 AFLR4 : Generate optimal mesh on surface definition 93 AFLR2 : Nodes, Trias,Quads= 57 78 0 AFLR4 : Nodes, Trias,Quads= 55 74 0 AFLR4 : Generate optimal mesh on surface definition 94 AFLR2 : Nodes, Trias,Quads= 135 188 0 AFLR4 : Nodes, Trias,Quads= 87 92 0 AFLR4 : Generate optimal mesh on surface definition 95 AFLR2 : Nodes, Trias,Quads= 32 41 0 AFLR4 : Nodes, Trias,Quads= 35 47 0 AFLR4 : Generate optimal mesh on surface definition 96 AFLR2 : Nodes, Trias,Quads= 34 43 0 AFLR4 : Nodes, Trias,Quads= 36 47 0 AFLR4 : Generate optimal mesh on surface definition 97 AFLR2 : Nodes, Trias,Quads= 175 245 0 AFLR4 : Nodes, Trias,Quads= 139 173 0 AFLR4 : Generate optimal mesh on surface definition 98 AFLR2 : Nodes, Trias,Quads= 32 40 0 AFLR4 : Nodes, Trias,Quads= 32 40 0 AFLR4 : Generate optimal mesh on surface definition 99 AFLR2 : Nodes, Trias,Quads= 303 516 0 AFLR4 : Nodes, Trias,Quads= 258 426 0 AFLR4 : Generate optimal mesh on surface definition 100 AFLR2 : Nodes, Trias,Quads= 380 642 0 AFLR4 : Nodes, Trias,Quads= 285 452 0 AFLR4 : Generate optimal mesh on surface definition 101 AFLR2 : Nodes, Trias,Quads= 334 560 0 AFLR4 : Nodes, Trias,Quads= 242 376 0 AFLR4 : Generate optimal mesh on surface definition 102 AFLR2 : Nodes, Trias,Quads= 271 457 0 AFLR4 : Nodes, Trias,Quads= 222 359 0 AFLR4 : Generate optimal mesh on surface definition 103 AFLR2 : Nodes, Trias,Quads= 369 622 0 AFLR4 : Nodes, Trias,Quads= 275 434 0 AFLR4 : Generate optimal mesh on surface definition 104 AFLR2 : Nodes, Trias,Quads= 272 459 0 AFLR4 : Nodes, Trias,Quads= 220 355 0 AFLR4 : Generate optimal mesh on surface definition 105 AFLR2 : Nodes, Trias,Quads= 303 516 0 AFLR4 : Nodes, Trias,Quads= 258 426 0 AFLR4 : Generate optimal mesh on surface definition 106 AFLR2 : Nodes, Trias,Quads= 353 594 0 AFLR4 : Nodes, Trias,Quads= 266 420 0 AFLR4 : Generate optimal mesh on surface definition 107 AFLR2 : Nodes, Trias,Quads= 72 113 0 AFLR4 : Nodes, Trias,Quads= 47 63 0 AFLR4 : Generate optimal mesh on surface definition 108 AFLR2 : Nodes, Trias,Quads= 70 109 0 AFLR4 : Nodes, Trias,Quads= 49 67 0 AFLR4 : Generate optimal mesh on surface definition 109 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 110 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 111 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 112 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 113 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 114 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 54881 109754 10706 AFLR4 : Proximity BG Surface Grid Generation AFLR4 : Nodes, Trias = 57112 114216 AFLR4 : Nodes, Trias = 57416 114824 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 779 1451 0 AFLR4 : Nodes, Trias,Quads= 643 1179 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 399 711 0 AFLR4 : Nodes, Trias,Quads= 375 663 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 753 1402 0 AFLR4 : Nodes, Trias,Quads= 682 1260 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 388 692 0 AFLR4 : Nodes, Trias,Quads= 357 630 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 773 1439 0 AFLR4 : Nodes, Trias,Quads= 640 1173 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 400 713 0 AFLR4 : Nodes, Trias,Quads= 373 659 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 751 1398 0 AFLR4 : Nodes, Trias,Quads= 681 1258 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 388 692 0 AFLR4 : Nodes, Trias,Quads= 358 632 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 21 27 0 AFLR4 : Nodes, Trias,Quads= 18 21 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 21 27 0 AFLR4 : Nodes, Trias,Quads= 20 25 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 66 90 0 AFLR4 : Nodes, Trias,Quads= 40 38 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 32 43 0 AFLR4 : Nodes, Trias,Quads= 29 37 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 32 43 0 AFLR4 : Nodes, Trias,Quads= 28 35 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 65 89 0 AFLR4 : Nodes, Trias,Quads= 39 37 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 61 80 0 AFLR4 : Nodes, Trias,Quads= 62 82 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 2575 4845 0 AFLR4 : Nodes, Trias,Quads= 2031 3757 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 109 150 0 AFLR4 : Nodes, Trias,Quads= 66 64 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 298 518 0 AFLR4 : Nodes, Trias,Quads= 228 378 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 62 81 0 AFLR4 : Nodes, Trias,Quads= 62 81 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 2640 4977 0 AFLR4 : Nodes, Trias,Quads= 2128 3953 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 39 50 0 AFLR4 : Nodes, Trias,Quads= 26 24 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 19 25 0 AFLR4 : Nodes, Trias,Quads= 19 25 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 2175 4085 0 AFLR4 : Nodes, Trias,Quads= 1917 3569 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 4841 9257 0 AFLR4 : Nodes, Trias,Quads= 3465 6505 0 AFLR4 : Generate optimal mesh on surface definition 25 AFLR2 : Nodes, Trias,Quads= 310 540 0 AFLR4 : Nodes, Trias,Quads= 242 404 0 AFLR4 : Generate optimal mesh on surface definition 26 AFLR2 : Nodes, Trias,Quads= 106 145 0 AFLR4 : Nodes, Trias,Quads= 65 63 0 AFLR4 : Generate optimal mesh on surface definition 27 AFLR2 : Nodes, Trias,Quads= 18 22 0 AFLR4 : Nodes, Trias,Quads= 19 24 0 AFLR4 : Generate optimal mesh on surface definition 28 AFLR2 : Nodes, Trias,Quads= 2233 4200 0 AFLR4 : Nodes, Trias,Quads= 1943 3620 0 AFLR4 : Generate optimal mesh on surface definition 29 AFLR2 : Nodes, Trias,Quads= 106 170 0 AFLR4 : Nodes, Trias,Quads= 120 198 0 AFLR4 : Generate optimal mesh on surface definition 30 AFLR2 : Nodes, Trias,Quads= 3808 7039 0 AFLR4 : Nodes, Trias,Quads= 4844 9111 0 AFLR4 : Generate optimal mesh on surface definition 31 AFLR2 : Nodes, Trias,Quads= 4921 9421 0 AFLR4 : Nodes, Trias,Quads= 3456 6491 0 AFLR4 : Generate optimal mesh on surface definition 32 AFLR2 : Nodes, Trias,Quads= 2589 4890 0 AFLR4 : Nodes, Trias,Quads= 1963 3638 0 AFLR4 : Generate optimal mesh on surface definition 33 AFLR2 : Nodes, Trias,Quads= 2216 4132 0 AFLR4 : Nodes, Trias,Quads= 2617 4934 0 AFLR4 : Generate optimal mesh on surface definition 34 AFLR2 : Nodes, Trias,Quads= 2344 4396 0 AFLR4 : Nodes, Trias,Quads= 1845 3398 0 AFLR4 : Generate optimal mesh on surface definition 35 AFLR2 : Nodes, Trias,Quads= 2657 5011 0 AFLR4 : Nodes, Trias,Quads= 2134 3965 0 AFLR4 : Generate optimal mesh on surface definition 36 AFLR2 : Nodes, Trias,Quads= 3830 7081 0 AFLR4 : Nodes, Trias,Quads= 4876 9173 0 AFLR4 : Generate optimal mesh on surface definition 37 AFLR2 : Nodes, Trias,Quads= 5597 10778 0 AFLR4 : Nodes, Trias,Quads= 3975 7534 0 AFLR4 : Generate optimal mesh on surface definition 38 AFLR2 : Nodes, Trias,Quads= 3935 7561 0 AFLR4 : Nodes, Trias,Quads= 2905 5501 0 AFLR4 : Generate optimal mesh on surface definition 39 AFLR2 : Nodes, Trias,Quads= 2618 4948 0 AFLR4 : Nodes, Trias,Quads= 2017 3746 0 AFLR4 : Generate optimal mesh on surface definition 40 AFLR2 : Nodes, Trias,Quads= 2217 4134 0 AFLR4 : Nodes, Trias,Quads= 2618 4936 0 AFLR4 : Generate optimal mesh on surface definition 41 AFLR2 : Nodes, Trias,Quads= 62 83 0 AFLR4 : Nodes, Trias,Quads= 39 37 0 AFLR4 : Generate optimal mesh on surface definition 42 AFLR2 : Nodes, Trias,Quads= 39 50 0 AFLR4 : Nodes, Trias,Quads= 26 24 0 AFLR4 : Generate optimal mesh on surface definition 43 AFLR2 : Nodes, Trias,Quads= 18 22 0 AFLR4 : Nodes, Trias,Quads= 19 24 0 AFLR4 : Generate optimal mesh on surface definition 44 AFLR2 : Nodes, Trias,Quads= 86 119 0 AFLR4 : Nodes, Trias,Quads= 51 49 0 AFLR4 : Generate optimal mesh on surface definition 45 AFLR2 : Nodes, Trias,Quads= 54 71 0 AFLR4 : Nodes, Trias,Quads= 58 79 0 AFLR4 : Generate optimal mesh on surface definition 46 AFLR2 : Nodes, Trias,Quads= 61 80 0 AFLR4 : Nodes, Trias,Quads= 62 82 0 AFLR4 : Generate optimal mesh on surface definition 47 AFLR2 : Nodes, Trias,Quads= 106 145 0 AFLR4 : Nodes, Trias,Quads= 65 63 0 AFLR4 : Generate optimal mesh on surface definition 48 AFLR2 : Nodes, Trias,Quads= 18 22 0 AFLR4 : Nodes, Trias,Quads= 19 24 0 AFLR4 : Generate optimal mesh on surface definition 49 AFLR2 : Nodes, Trias,Quads= 3946 7581 0 AFLR4 : Nodes, Trias,Quads= 2941 5571 0 AFLR4 : Generate optimal mesh on surface definition 50 AFLR2 : Nodes, Trias,Quads= 5414 10410 0 AFLR4 : Nodes, Trias,Quads= 3958 7498 0 AFLR4 : Generate optimal mesh on surface definition 51 AFLR2 : Nodes, Trias,Quads= 62 92 0 AFLR4 : Nodes, Trias,Quads= 45 58 0 AFLR4 : Generate optimal mesh on surface definition 52 AFLR2 : Nodes, Trias,Quads= 127 168 0 AFLR4 : Nodes, Trias,Quads= 120 154 0 AFLR4 : Generate optimal mesh on surface definition 53 AFLR2 : Nodes, Trias,Quads= 58 85 0 AFLR4 : Nodes, Trias,Quads= 44 57 0 AFLR4 : Generate optimal mesh on surface definition 54 AFLR2 : Nodes, Trias,Quads= 5057 9716 0 AFLR4 : Nodes, Trias,Quads= 2994 5590 0 AFLR4 : Generate optimal mesh on surface definition 55 AFLR2 : Nodes, Trias,Quads= 4633 8888 0 AFLR4 : Nodes, Trias,Quads= 2623 4868 0 AFLR4 : Generate optimal mesh on surface definition 56 AFLR2 : Nodes, Trias,Quads= 88 138 0 AFLR4 : Nodes, Trias,Quads= 54 70 0 AFLR4 : Generate optimal mesh on surface definition 57 AFLR2 : Nodes, Trias,Quads= 198 270 0 AFLR4 : Nodes, Trias,Quads= 204 282 0 AFLR4 : Generate optimal mesh on surface definition 58 AFLR2 : Nodes, Trias,Quads= 76 117 0 AFLR4 : Nodes, Trias,Quads= 49 63 0 AFLR4 : Generate optimal mesh on surface definition 59 AFLR2 : Nodes, Trias,Quads= 234 399 0 AFLR4 : Nodes, Trias,Quads= 188 307 0 AFLR4 : Generate optimal mesh on surface definition 60 AFLR2 : Nodes, Trias,Quads= 293 507 0 AFLR4 : Nodes, Trias,Quads= 234 389 0 AFLR4 : Generate optimal mesh on surface definition 61 AFLR2 : Nodes, Trias,Quads= 4681 8974 0 AFLR4 : Nodes, Trias,Quads= 2721 5054 0 AFLR4 : Generate optimal mesh on surface definition 62 AFLR2 : Nodes, Trias,Quads= 87 136 0 AFLR4 : Nodes, Trias,Quads= 54 70 0 AFLR4 : Generate optimal mesh on surface definition 63 AFLR2 : Nodes, Trias,Quads= 205 284 0 AFLR4 : Nodes, Trias,Quads= 195 264 0 AFLR4 : Generate optimal mesh on surface definition 64 AFLR2 : Nodes, Trias,Quads= 76 117 0 AFLR4 : Nodes, Trias,Quads= 50 65 0 AFLR4 : Generate optimal mesh on surface definition 65 AFLR2 : Nodes, Trias,Quads= 62 92 0 AFLR4 : Nodes, Trias,Quads= 46 60 0 AFLR4 : Generate optimal mesh on surface definition 66 AFLR2 : Nodes, Trias,Quads= 138 190 0 AFLR4 : Nodes, Trias,Quads= 127 168 0 AFLR4 : Generate optimal mesh on surface definition 67 AFLR2 : Nodes, Trias,Quads= 62 92 0 AFLR4 : Nodes, Trias,Quads= 46 60 0 AFLR4 : Generate optimal mesh on surface definition 68 AFLR2 : Nodes, Trias,Quads= 4678 8970 0 AFLR4 : Nodes, Trias,Quads= 2893 5400 0 AFLR4 : Generate optimal mesh on surface definition 69 AFLR2 : Nodes, Trias,Quads= 350 608 0 AFLR4 : Nodes, Trias,Quads= 324 556 0 AFLR4 : Generate optimal mesh on surface definition 70 AFLR2 : Nodes, Trias,Quads= 70 101 0 AFLR4 : Nodes, Trias,Quads= 62 85 0 AFLR4 : Generate optimal mesh on surface definition 71 AFLR2 : Nodes, Trias,Quads= 149 207 0 AFLR4 : Nodes, Trias,Quads= 95 99 0 AFLR4 : Generate optimal mesh on surface definition 72 AFLR2 : Nodes, Trias,Quads= 36 46 0 AFLR4 : Nodes, Trias,Quads= 38 50 0 AFLR4 : Generate optimal mesh on surface definition 73 AFLR2 : Nodes, Trias,Quads= 50 67 0 AFLR4 : Nodes, Trias,Quads= 48 63 0 AFLR4 : Generate optimal mesh on surface definition 74 AFLR2 : Nodes, Trias,Quads= 220 305 0 AFLR4 : Nodes, Trias,Quads= 209 283 0 AFLR4 : Generate optimal mesh on surface definition 75 AFLR2 : Nodes, Trias,Quads= 31 39 0 AFLR4 : Nodes, Trias,Quads= 31 39 0 AFLR4 : Generate optimal mesh on surface definition 76 AFLR2 : Nodes, Trias,Quads= 39 50 0 AFLR4 : Nodes, Trias,Quads= 26 24 0 AFLR4 : Generate optimal mesh on surface definition 77 AFLR2 : Nodes, Trias,Quads= 32 40 0 AFLR4 : Nodes, Trias,Quads= 33 42 0 AFLR4 : Generate optimal mesh on surface definition 78 AFLR2 : Nodes, Trias,Quads= 196 279 0 AFLR4 : Nodes, Trias,Quads= 113 113 0 AFLR4 : Generate optimal mesh on surface definition 79 AFLR2 : Nodes, Trias,Quads= 35 45 0 AFLR4 : Nodes, Trias,Quads= 38 51 0 AFLR4 : Generate optimal mesh on surface definition 80 AFLR2 : Nodes, Trias,Quads= 36 46 0 AFLR4 : Nodes, Trias,Quads= 36 46 0 AFLR4 : Generate optimal mesh on surface definition 81 AFLR2 : Nodes, Trias,Quads= 157 225 0 AFLR4 : Nodes, Trias,Quads= 95 101 0 AFLR4 : Generate optimal mesh on surface definition 82 AFLR2 : Nodes, Trias,Quads= 47 63 0 AFLR4 : Nodes, Trias,Quads= 46 61 0 AFLR4 : Generate optimal mesh on surface definition 83 AFLR2 : Nodes, Trias,Quads= 520 923 0 AFLR4 : Nodes, Trias,Quads= 508 899 0 AFLR4 : Generate optimal mesh on surface definition 84 AFLR2 : Nodes, Trias,Quads= 39 50 0 AFLR4 : Nodes, Trias,Quads= 26 24 0 AFLR4 : Generate optimal mesh on surface definition 85 AFLR2 : Nodes, Trias,Quads= 32 41 0 AFLR4 : Nodes, Trias,Quads= 31 39 0 AFLR4 : Generate optimal mesh on surface definition 86 AFLR2 : Nodes, Trias,Quads= 199 273 0 AFLR4 : Nodes, Trias,Quads= 152 179 0 AFLR4 : Generate optimal mesh on surface definition 87 AFLR2 : Nodes, Trias,Quads= 51 69 0 AFLR4 : Nodes, Trias,Quads= 48 63 0 AFLR4 : Generate optimal mesh on surface definition 88 AFLR2 : Nodes, Trias,Quads= 37 47 0 AFLR4 : Nodes, Trias,Quads= 41 55 0 AFLR4 : Generate optimal mesh on surface definition 89 AFLR2 : Nodes, Trias,Quads= 159 229 0 AFLR4 : Nodes, Trias,Quads= 95 101 0 AFLR4 : Generate optimal mesh on surface definition 90 AFLR2 : Nodes, Trias,Quads= 46 61 0 AFLR4 : Nodes, Trias,Quads= 46 61 0 AFLR4 : Generate optimal mesh on surface definition 91 AFLR2 : Nodes, Trias,Quads= 515 913 0 AFLR4 : Nodes, Trias,Quads= 504 891 0 AFLR4 : Generate optimal mesh on surface definition 92 AFLR2 : Nodes, Trias,Quads= 354 616 0 AFLR4 : Nodes, Trias,Quads= 320 548 0 AFLR4 : Generate optimal mesh on surface definition 93 AFLR2 : Nodes, Trias,Quads= 70 101 0 AFLR4 : Nodes, Trias,Quads= 62 85 0 AFLR4 : Generate optimal mesh on surface definition 94 AFLR2 : Nodes, Trias,Quads= 140 190 0 AFLR4 : Nodes, Trias,Quads= 96 102 0 AFLR4 : Generate optimal mesh on surface definition 95 AFLR2 : Nodes, Trias,Quads= 34 44 0 AFLR4 : Nodes, Trias,Quads= 35 46 0 AFLR4 : Generate optimal mesh on surface definition 96 AFLR2 : Nodes, Trias,Quads= 36 47 0 AFLR4 : Nodes, Trias,Quads= 37 49 0 AFLR4 : Generate optimal mesh on surface definition 97 AFLR2 : Nodes, Trias,Quads= 204 286 0 AFLR4 : Nodes, Trias,Quads= 165 208 0 AFLR4 : Generate optimal mesh on surface definition 98 AFLR2 : Nodes, Trias,Quads= 32 40 0 AFLR4 : Nodes, Trias,Quads= 34 44 0 AFLR4 : Generate optimal mesh on surface definition 99 AFLR2 : Nodes, Trias,Quads= 344 591 0 AFLR4 : Nodes, Trias,Quads= 292 487 0 AFLR4 : Generate optimal mesh on surface definition 100 AFLR2 : Nodes, Trias,Quads= 442 755 0 AFLR4 : Nodes, Trias,Quads= 340 551 0 AFLR4 : Generate optimal mesh on surface definition 101 AFLR2 : Nodes, Trias,Quads= 377 638 0 AFLR4 : Nodes, Trias,Quads= 268 420 0 AFLR4 : Generate optimal mesh on surface definition 102 AFLR2 : Nodes, Trias,Quads= 327 559 0 AFLR4 : Nodes, Trias,Quads= 273 451 0 AFLR4 : Generate optimal mesh on surface definition 103 AFLR2 : Nodes, Trias,Quads= 419 714 0 AFLR4 : Nodes, Trias,Quads= 304 484 0 AFLR4 : Generate optimal mesh on surface definition 104 AFLR2 : Nodes, Trias,Quads= 326 557 0 AFLR4 : Nodes, Trias,Quads= 271 447 0 AFLR4 : Generate optimal mesh on surface definition 105 AFLR2 : Nodes, Trias,Quads= 345 593 0 AFLR4 : Nodes, Trias,Quads= 292 487 0 AFLR4 : Generate optimal mesh on surface definition 106 AFLR2 : Nodes, Trias,Quads= 409 698 0 AFLR4 : Nodes, Trias,Quads= 301 482 0 AFLR4 : Generate optimal mesh on surface definition 107 AFLR2 : Nodes, Trias,Quads= 89 141 0 AFLR4 : Nodes, Trias,Quads= 66 95 0 AFLR4 : Generate optimal mesh on surface definition 108 AFLR2 : Nodes, Trias,Quads= 94 150 0 AFLR4 : Nodes, Trias,Quads= 67 96 0 AFLR4 : Generate optimal mesh on surface definition 109 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 110 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 111 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 112 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 113 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 114 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 69451 138894 13136 OVERALL : CPU Time = 7.622 seconds Body 1 (of 4) Number of nodes = 1866 Number of elements = 3732 Number of triangle elements = 3732 Number of quadrilateral elements = 0 Body 2 (of 4) Number of nodes = 1861 Number of elements = 3722 Number of triangle elements = 3722 Number of quadrilateral elements = 0 Body 3 (of 4) Number of nodes = 65404 Number of elements = 130804 Number of triangle elements = 130804 Number of quadrilateral elements = 0 Body 4 (of 4) Number of nodes = 320 Number of elements = 636 Number of triangle elements = 636 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 69451 Total number of elements = 138894 Total number of triangle elements = 138894 Total number of quadrilateral elements = 0 real 1m26.294s user 1m30.751s sys 0m6.154s + status=0 + set +x ================================================= data/session07/08_aflr4_InviscidTransport.py passed (as expected) ================================================= ================================================= 09_aflr4_aflr3_InviscidWing.py test; + python 09_aflr4_aflr3_InviscidWing.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml MESSAGE:: Building nacelleOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Nacelle, index = 1 Name = Wing, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Nacelle, index = 1 Name = leftWing, index = 2 Name = riteWing, index = 3 Name = Farfield, index = 4 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - leftWing Mesh sizing name - riteWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 4 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 4 Faces EGADS : Body 0 has 8 Edges EGADS : Body 0 has 4 Loops EGADS : Body 0 has 4 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 4 Faces EGADS : Body 1 has 8 Edges EGADS : Body 1 has 4 Loops EGADS : Body 1 has 4 Nodes EGADS : Body 2 is a SolidBody EGADS : Body 2 has 1 Shells EGADS : Body 2 has 10 Faces EGADS : Body 2 has 18 Edges EGADS : Body 2 has 10 Loops EGADS : Body 2 has 10 Nodes EGADS : Body 3 is a SolidBody EGADS : Body 3 has 1 Shells EGADS : Body 3 has 6 Faces EGADS : Body 3 has 12 Edges EGADS : Body 3 has 6 Loops EGADS : Body 3 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 EGADS : 2 Yes 0 0 1 0 1 1 4 EGADS : 3 Yes 0 0 1 0 1 1 4 EGADS : 4 Yes 0 0 1 0 1 2 3 EGADS : 5 Yes 1 0 1 0 1 6 7 EGADS : 6 Yes 1 0 1 0 1 5 8 EGADS : 7 Yes 1 0 1 0 1 5 8 EGADS : 8 Yes 1 0 1 0 1 6 7 EGADS : 9 Yes 2 0 1 1 1 10 11 14 EGADS : 10 Yes 2 0 1 1 1 9 12 13 EGADS : 11 Yes 2 0 1 1 1 9 12 16 EGADS : 12 Yes 2 0 1 1 1 10 11 13 EGADS : 13 Yes 2 0 1 1 1 10 12 EGADS : 14 Yes 2 0 1 1 1 9 15 16 EGADS : 15 Yes 2 0 1 1 1 14 17 18 EGADS : 16 Yes 2 0 1 1 1 11 14 17 EGADS : 17 Yes 2 0 1 1 1 15 16 18 EGADS : 18 Yes 2 0 1 1 1 15 17 EGADS : 19 Yes 3 0 1 NA NA 21 22 23 24 EGADS : 20 Yes 3 0 1 NA NA 21 22 23 24 EGADS : 21 Yes 3 0 1 NA NA 19 20 23 24 EGADS : 22 Yes 3 0 1 NA NA 19 20 23 24 EGADS : 23 Yes 3 0 1 NA NA 19 20 21 22 EGADS : 24 Yes 3 0 1 NA NA 19 20 21 22 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 3 2 -4 EGADS : 2 -2 5 1 -6 EGADS : 3 7 4 -8 -3 EGADS : 4 8 6 -7 -5 EGADS : 5 9 12 -10 -11 EGADS : 6 10 14 -9 -13 EGADS : 7 -15 11 16 -12 EGADS : 8 -16 13 15 -14 EGADS : 9 -17 18 19 -20 EGADS : 10 -21 20 22 -23 EGADS : 11 -19 24 17 -25 EGADS : 12 -22 25 21 -26 EGADS : 13 23 26 EGADS : 14 27 29 -28 -18 EGADS : 15 30 32 -31 -29 EGADS : 16 28 33 -27 -24 EGADS : 17 31 34 -30 -33 EGADS : 18 -32 -34 EGADS : 19 35 36 -37 -38 EGADS : 20 -39 42 41 -40 EGADS : 21 43 39 -44 -35 EGADS : 22 -45 37 46 -41 EGADS : 23 38 45 -42 -43 EGADS : 24 -36 44 40 -46 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : 17 17 EGADS : 18 18 EGADS : 19 19 EGADS : 20 20 EGADS : 21 21 EGADS : 22 22 EGADS : 23 23 EGADS : 24 24 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 3 2 -4 EGADS : 2 Yes -2 5 1 -6 EGADS : 3 Yes 7 4 -8 -3 EGADS : 4 Yes 8 6 -7 -5 EGADS : 5 Yes 9 12 -10 -11 EGADS : 6 Yes 10 14 -9 -13 EGADS : 7 Yes -15 11 16 -12 EGADS : 8 Yes -16 13 15 -14 EGADS : 9 Yes -17 18 19 -20 EGADS : 10 Yes -21 20 22 -23 EGADS : 11 Yes -19 24 17 -25 EGADS : 12 Yes -22 25 21 -26 EGADS : 13 Yes 23 26 EGADS : 14 Yes 27 29 -28 -18 EGADS : 15 Yes 30 32 -31 -29 EGADS : 16 Yes 28 33 -27 -24 EGADS : 17 Yes 31 34 -30 -33 EGADS : 18 Yes -32 -34 EGADS : 19 Yes 35 36 -37 -38 EGADS : 20 Yes -39 42 41 -40 EGADS : 21 Yes 43 39 -44 -35 EGADS : 22 Yes -45 37 46 -41 EGADS : 23 Yes 38 45 -42 -43 EGADS : 24 Yes -36 44 40 -46 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 2 EGADS : 2 0 Yes 3 4 1 1 2 EGADS : 3 0 Yes 1 3 1 1 3 EGADS : 4 0 Yes 2 4 1 1 3 EGADS : 5 0 Yes 3 1 1 2 4 EGADS : 6 0 Yes 4 2 1 2 4 EGADS : 7 0 Yes 1 2 1 3 4 EGADS : 8 0 Yes 3 4 1 3 4 EGADS : 9 1 Yes 5 6 1 5 6 EGADS : 10 1 Yes 7 8 1 5 6 EGADS : 11 1 Yes 5 7 1 5 7 EGADS : 12 1 Yes 6 8 1 5 7 EGADS : 13 1 Yes 7 5 1 6 8 EGADS : 14 1 Yes 8 6 1 6 8 EGADS : 15 1 Yes 5 6 1 7 8 EGADS : 16 1 Yes 7 8 1 7 8 EGADS : 17 2 Yes 9 10 1 9 11 EGADS : 18 2 Yes 9 11 1 9 14 EGADS : 19 2 Yes 11 12 1 9 11 EGADS : 20 2 Yes 10 12 1 9 10 EGADS : 21 2 Yes 10 13 1 10 12 EGADS : 22 2 Yes 12 14 1 10 12 EGADS : 23 2 Yes 13 14 1 10 13 EGADS : 24 2 Yes 11 9 1 11 16 EGADS : 25 2 Yes 12 10 1 11 12 EGADS : 26 2 Yes 14 13 1 12 13 EGADS : 27 2 Yes 9 15 1 14 16 EGADS : 28 2 Yes 11 16 1 14 16 EGADS : 29 2 Yes 15 16 1 14 15 EGADS : 30 2 Yes 15 17 1 15 17 EGADS : 31 2 Yes 16 18 1 15 17 EGADS : 32 2 Yes 17 18 1 15 18 EGADS : 33 2 Yes 16 15 1 16 17 EGADS : 34 2 Yes 18 17 1 17 18 EGADS : 35 3 Yes 20 19 NA 19 21 EGADS : 36 3 Yes 19 21 NA 19 24 EGADS : 37 3 Yes 22 21 NA 19 22 EGADS : 38 3 Yes 20 22 NA 19 23 EGADS : 39 3 Yes 24 23 NA 20 21 EGADS : 40 3 Yes 23 25 NA 20 24 EGADS : 41 3 Yes 26 25 NA 20 22 EGADS : 42 3 Yes 24 26 NA 20 23 EGADS : 43 3 Yes 20 24 NA 21 23 EGADS : 44 3 Yes 19 23 NA 21 24 EGADS : 45 3 Yes 22 26 NA 22 23 EGADS : 46 3 Yes 21 25 NA 22 24 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 90.5173952 0 0 EGADS : 2 Yes 90.5173952 0 0 EGADS : 3 Yes 60.5173952 0 0 EGADS : 4 Yes 60.5173952 0 0 EGADS : 5 Yes 90.5173952 29.3018771 0 EGADS : 6 Yes 90.5173952 29.3018771 0 EGADS : 7 Yes 60.5173952 29.3018771 0 EGADS : 8 Yes 60.5173952 29.3018771 0 EGADS : 9 Yes 97.2007855 0 0 EGADS : 10 Yes 97.9335611 0 0 EGADS : 11 Yes 50 0 0 EGADS : 12 Yes 75.3047874 0 0 EGADS : 13 Yes 123.552357 0 4.7180639 EGADS : 14 Yes 118.391317 0 3.99272703 EGADS : 15 Yes 97.9335611 36.1389817 0 EGADS : 16 Yes 75.3047874 36.1389817 0 EGADS : 17 Yes 123.552357 97.6729236 4.7180639 EGADS : 18 Yes 118.391317 97.6729236 3.99272703 EGADS : 19 Yes 0 0 1947.05079 EGADS : 20 Yes 0 0 0 EGADS : 21 Yes 0 1953.45847 1947.05079 EGADS : 22 Yes 0 1953.45847 0 EGADS : 23 Yes 2040.21562 0 1947.05079 EGADS : 24 Yes 2040.21562 0 0 EGADS : 25 Yes 2040.21562 1953.45847 1947.05079 EGADS : 26 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 22.2515 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 2651.51 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 5 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 STD w/BL AFLR4 : 12 CAD geometry 0 STD w/BL AFLR4 : 13 CAD geometry 0 STD w/BL AFLR4 : 14 CAD geometry 0 STD w/BL AFLR4 : 15 CAD geometry 0 STD w/BL AFLR4 : 16 CAD geometry 0 STD w/BL AFLR4 : 17 CAD geometry 0 STD w/BL AFLR4 : 18 CAD geometry 0 STD w/BL AFLR4 : 19 CAD geometry 0 FARFIELD AFLR4 : 20 CAD geometry 0 FARFIELD AFLR4 : 21 CAD geometry 0 FARFIELD AFLR4 : 22 CAD geometry 0 FARFIELD AFLR4 : 23 CAD geometry 0 FARFIELD AFLR4 : 24 CAD geometry 0 FARFIELD AFLR4 : Case has 2 Proximity Checking Components AFLR4 : Component 1 includes Definitions 9 10 11 12 13 14 15 16 17 18 AFLR4 : Component 2 includes Definitions 1 2 3 4 5 6 7 8 AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Define CAD surface definition 17 AFLR4 : Define CAD surface definition 18 AFLR4 : Define CAD surface definition 19 AFLR4 : Define CAD surface definition 20 AFLR4 : Define CAD surface definition 21 AFLR4 : Define CAD surface definition 22 AFLR4 : Define CAD surface definition 23 AFLR4 : Define CAD surface definition 24 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 339 605 0 AFLR4 : Nodes, Trias,Quads= 362 651 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 319 563 0 AFLR4 : Nodes, Trias,Quads= 284 493 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 340 607 0 AFLR4 : Nodes, Trias,Quads= 362 651 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 321 567 0 AFLR4 : Nodes, Trias,Quads= 284 493 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 340 607 0 AFLR4 : Nodes, Trias,Quads= 362 651 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 321 567 0 AFLR4 : Nodes, Trias,Quads= 284 493 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 339 605 0 AFLR4 : Nodes, Trias,Quads= 362 651 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 319 563 0 AFLR4 : Nodes, Trias,Quads= 284 493 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 1107 2082 0 AFLR4 : Nodes, Trias,Quads= 685 1238 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 1473 2759 0 AFLR4 : Nodes, Trias,Quads= 721 1255 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 1116 2100 0 AFLR4 : Nodes, Trias,Quads= 671 1210 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 1458 2729 0 AFLR4 : Nodes, Trias,Quads= 714 1241 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 20 24 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 1108 2084 0 AFLR4 : Nodes, Trias,Quads= 683 1234 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 1488 2789 0 AFLR4 : Nodes, Trias,Quads= 714 1241 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 1112 2092 0 AFLR4 : Nodes, Trias,Quads= 653 1174 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 1456 2725 0 AFLR4 : Nodes, Trias,Quads= 708 1229 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 20 24 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 7221 14434 1888 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 7221 14434 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 397 713 0 AFLR4 : Nodes, Trias,Quads= 416 751 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 387 691 0 AFLR4 : Nodes, Trias,Quads= 346 609 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 396 711 0 AFLR4 : Nodes, Trias,Quads= 417 753 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 388 693 0 AFLR4 : Nodes, Trias,Quads= 344 605 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 395 709 0 AFLR4 : Nodes, Trias,Quads= 416 751 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 388 693 0 AFLR4 : Nodes, Trias,Quads= 344 605 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 395 709 0 AFLR4 : Nodes, Trias,Quads= 416 751 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 387 691 0 AFLR4 : Nodes, Trias,Quads= 346 609 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 12796 24695 0 AFLR4 : Nodes, Trias,Quads= 7764 14631 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 29245 57075 0 AFLR4 : Nodes, Trias,Quads= 12448 23481 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 12136 23411 0 AFLR4 : Nodes, Trias,Quads= 7447 14033 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 29424 57435 0 AFLR4 : Nodes, Trias,Quads= 12399 23385 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 196 293 0 AFLR4 : Nodes, Trias,Quads= 188 277 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 12819 24741 0 AFLR4 : Nodes, Trias,Quads= 7725 14553 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 29449 57483 0 AFLR4 : Nodes, Trias,Quads= 12413 23411 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 12144 23427 0 AFLR4 : Nodes, Trias,Quads= 7471 14081 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 29445 57477 0 AFLR4 : Nodes, Trias,Quads= 12478 23543 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 196 293 0 AFLR4 : Nodes, Trias,Quads= 188 277 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 78575 157142 10038 AFLR4 : Proximity BG Surface Grid Generation AFLR4 : Nodes, Trias = 78961 157914 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 850 1593 0 AFLR4 : Nodes, Trias,Quads= 754 1401 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 384 685 0 AFLR4 : Nodes, Trias,Quads= 354 625 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 842 1577 0 AFLR4 : Nodes, Trias,Quads= 803 1499 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 384 685 0 AFLR4 : Nodes, Trias,Quads= 351 619 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 837 1566 0 AFLR4 : Nodes, Trias,Quads= 755 1402 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 384 685 0 AFLR4 : Nodes, Trias,Quads= 352 621 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 834 1560 0 AFLR4 : Nodes, Trias,Quads= 806 1504 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 384 685 0 AFLR4 : Nodes, Trias,Quads= 353 623 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 11687 22537 0 AFLR4 : Nodes, Trias,Quads= 9244 17651 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 22200 43075 0 AFLR4 : Nodes, Trias,Quads= 14790 28255 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 11200 21594 0 AFLR4 : Nodes, Trias,Quads= 8943 17080 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 22061 42799 0 AFLR4 : Nodes, Trias,Quads= 14755 28187 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 179 265 0 AFLR4 : Nodes, Trias,Quads= 177 261 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 11697 22557 0 AFLR4 : Nodes, Trias,Quads= 9237 17637 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 22392 43459 0 AFLR4 : Nodes, Trias,Quads= 14703 28081 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 11243 21680 0 AFLR4 : Nodes, Trias,Quads= 8970 17134 0 AFLR4 : Generate optimal mesh on surface definition 17 AFLR2 : Nodes, Trias,Quads= 22235 43146 0 AFLR4 : Nodes, Trias,Quads= 14758 28192 0 AFLR4 : Generate optimal mesh on surface definition 18 AFLR2 : Nodes, Trias,Quads= 184 274 0 AFLR4 : Nodes, Trias,Quads= 179 264 0 AFLR4 : Generate optimal mesh on surface definition 19 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 20 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 21 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 22 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 23 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 24 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 95540 191072 9544 OVERALL : CPU Time = 5.982 seconds Body 1 (of 4) Number of nodes = 2072 Number of elements = 4144 Number of triangle elements = 4144 Number of quadrilateral elements = 0 Body 2 (of 4) Number of nodes = 2075 Number of elements = 4150 Number of triangle elements = 4150 Number of quadrilateral elements = 0 Body 3 (of 4) Number of nodes = 91373 Number of elements = 182742 Number of triangle elements = 182742 Number of quadrilateral elements = 0 Body 4 (of 4) Number of nodes = 20 Number of elements = 36 Number of triangle elements = 36 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 95540 Total number of elements = 191072 Total number of triangle elements = 191072 Total number of quadrilateral elements = 0 Writing vtk file .... Writing vtk surface file .... capsGroups found: 1: Nacelle 2: Wing 3: Farfield Finished writing vtk file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Nacelle, index = 1 Name = leftWing, index = 2 Name = riteWing, index = 3 Name = Farfield, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Nacelle, index = 1 Name = Wing, index = 2 Name = Farfield, index = 3 Getting volume mesh UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 4 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 4 Faces EGADS : Body 0 has 8 Edges EGADS : Body 0 has 4 Loops EGADS : Body 0 has 4 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 4 Faces EGADS : Body 1 has 8 Edges EGADS : Body 1 has 4 Loops EGADS : Body 1 has 4 Nodes EGADS : Body 2 is a SolidBody EGADS : Body 2 has 1 Shells EGADS : Body 2 has 10 Faces EGADS : Body 2 has 18 Edges EGADS : Body 2 has 10 Loops EGADS : Body 2 has 10 Nodes EGADS : Body 3 is a SolidBody EGADS : Body 3 has 1 Shells EGADS : Body 3 has 6 Faces EGADS : Body 3 has 12 Edges EGADS : Body 3 has 6 Loops EGADS : Body 3 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 EGADS : 2 Yes 0 0 1 0 1 1 4 EGADS : 3 Yes 0 0 1 0 1 1 4 EGADS : 4 Yes 0 0 1 0 1 2 3 EGADS : 5 Yes 1 0 1 0 1 6 7 EGADS : 6 Yes 1 0 1 0 1 5 8 EGADS : 7 Yes 1 0 1 0 1 5 8 EGADS : 8 Yes 1 0 1 0 1 6 7 EGADS : 9 Yes 2 0 1 1 1 10 11 14 EGADS : 10 Yes 2 0 1 1 1 9 12 13 EGADS : 11 Yes 2 0 1 1 1 9 12 16 EGADS : 12 Yes 2 0 1 1 1 10 11 13 EGADS : 13 Yes 2 0 1 1 1 10 12 EGADS : 14 Yes 2 0 1 1 1 9 15 16 EGADS : 15 Yes 2 0 1 1 1 14 17 18 EGADS : 16 Yes 2 0 1 1 1 11 14 17 EGADS : 17 Yes 2 0 1 1 1 15 16 18 EGADS : 18 Yes 2 0 1 1 1 15 17 EGADS : 19 Yes 3 0 1 NA NA 21 22 23 24 EGADS : 20 Yes 3 0 1 NA NA 21 22 23 24 EGADS : 21 Yes 3 0 1 NA NA 19 20 23 24 EGADS : 22 Yes 3 0 1 NA NA 19 20 23 24 EGADS : 23 Yes 3 0 1 NA NA 19 20 21 22 EGADS : 24 Yes 3 0 1 NA NA 19 20 21 22 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 3 2 -4 EGADS : 2 -2 5 1 -6 EGADS : 3 7 4 -8 -3 EGADS : 4 8 6 -7 -5 EGADS : 5 9 12 -10 -11 EGADS : 6 10 14 -9 -13 EGADS : 7 -15 11 16 -12 EGADS : 8 -16 13 15 -14 EGADS : 9 -17 18 19 -20 EGADS : 10 -21 20 22 -23 EGADS : 11 -19 24 17 -25 EGADS : 12 -22 25 21 -26 EGADS : 13 23 26 EGADS : 14 27 29 -28 -18 EGADS : 15 30 32 -31 -29 EGADS : 16 28 33 -27 -24 EGADS : 17 31 34 -30 -33 EGADS : 18 -32 -34 EGADS : 19 35 36 -37 -38 EGADS : 20 -39 42 41 -40 EGADS : 21 43 39 -44 -35 EGADS : 22 -45 37 46 -41 EGADS : 23 38 45 -42 -43 EGADS : 24 -36 44 40 -46 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : 17 17 EGADS : 18 18 EGADS : 19 19 EGADS : 20 20 EGADS : 21 21 EGADS : 22 22 EGADS : 23 23 EGADS : 24 24 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 3 2 -4 EGADS : 2 Yes -2 5 1 -6 EGADS : 3 Yes 7 4 -8 -3 EGADS : 4 Yes 8 6 -7 -5 EGADS : 5 Yes 9 12 -10 -11 EGADS : 6 Yes 10 14 -9 -13 EGADS : 7 Yes -15 11 16 -12 EGADS : 8 Yes -16 13 15 -14 EGADS : 9 Yes -17 18 19 -20 EGADS : 10 Yes -21 20 22 -23 EGADS : 11 Yes -19 24 17 -25 EGADS : 12 Yes -22 25 21 -26 EGADS : 13 Yes 23 26 EGADS : 14 Yes 27 29 -28 -18 EGADS : 15 Yes 30 32 -31 -29 EGADS : 16 Yes 28 33 -27 -24 EGADS : 17 Yes 31 34 -30 -33 EGADS : 18 Yes -32 -34 EGADS : 19 Yes 35 36 -37 -38 EGADS : 20 Yes -39 42 41 -40 EGADS : 21 Yes 43 39 -44 -35 EGADS : 22 Yes -45 37 46 -41 EGADS : 23 Yes 38 45 -42 -43 EGADS : 24 Yes -36 44 40 -46 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 2 EGADS : 2 0 Yes 3 4 1 1 2 EGADS : 3 0 Yes 1 3 1 1 3 EGADS : 4 0 Yes 2 4 1 1 3 EGADS : 5 0 Yes 3 1 1 2 4 EGADS : 6 0 Yes 4 2 1 2 4 EGADS : 7 0 Yes 1 2 1 3 4 EGADS : 8 0 Yes 3 4 1 3 4 EGADS : 9 1 Yes 5 6 1 5 6 EGADS : 10 1 Yes 7 8 1 5 6 EGADS : 11 1 Yes 5 7 1 5 7 EGADS : 12 1 Yes 6 8 1 5 7 EGADS : 13 1 Yes 7 5 1 6 8 EGADS : 14 1 Yes 8 6 1 6 8 EGADS : 15 1 Yes 5 6 1 7 8 EGADS : 16 1 Yes 7 8 1 7 8 EGADS : 17 2 Yes 9 10 1 9 11 EGADS : 18 2 Yes 9 11 1 9 14 EGADS : 19 2 Yes 11 12 1 9 11 EGADS : 20 2 Yes 10 12 1 9 10 EGADS : 21 2 Yes 10 13 1 10 12 EGADS : 22 2 Yes 12 14 1 10 12 EGADS : 23 2 Yes 13 14 1 10 13 EGADS : 24 2 Yes 11 9 1 11 16 EGADS : 25 2 Yes 12 10 1 11 12 EGADS : 26 2 Yes 14 13 1 12 13 EGADS : 27 2 Yes 9 15 1 14 16 EGADS : 28 2 Yes 11 16 1 14 16 EGADS : 29 2 Yes 15 16 1 14 15 EGADS : 30 2 Yes 15 17 1 15 17 EGADS : 31 2 Yes 16 18 1 15 17 EGADS : 32 2 Yes 17 18 1 15 18 EGADS : 33 2 Yes 16 15 1 16 17 EGADS : 34 2 Yes 18 17 1 17 18 EGADS : 35 3 Yes 20 19 NA 19 21 EGADS : 36 3 Yes 19 21 NA 19 24 EGADS : 37 3 Yes 22 21 NA 19 22 EGADS : 38 3 Yes 20 22 NA 19 23 EGADS : 39 3 Yes 24 23 NA 20 21 EGADS : 40 3 Yes 23 25 NA 20 24 EGADS : 41 3 Yes 26 25 NA 20 22 EGADS : 42 3 Yes 24 26 NA 20 23 EGADS : 43 3 Yes 20 24 NA 21 23 EGADS : 44 3 Yes 19 23 NA 21 24 EGADS : 45 3 Yes 22 26 NA 22 23 EGADS : 46 3 Yes 21 25 NA 22 24 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 90.5173952 0 0 EGADS : 2 Yes 90.5173952 0 0 EGADS : 3 Yes 60.5173952 0 0 EGADS : 4 Yes 60.5173952 0 0 EGADS : 5 Yes 90.5173952 29.3018771 0 EGADS : 6 Yes 90.5173952 29.3018771 0 EGADS : 7 Yes 60.5173952 29.3018771 0 EGADS : 8 Yes 60.5173952 29.3018771 0 EGADS : 9 Yes 97.2007855 0 0 EGADS : 10 Yes 97.9335611 0 0 EGADS : 11 Yes 50 0 0 EGADS : 12 Yes 75.3047874 0 0 EGADS : 13 Yes 123.552357 0 4.7180639 EGADS : 14 Yes 118.391317 0 3.99272703 EGADS : 15 Yes 97.9335611 36.1389817 0 EGADS : 16 Yes 75.3047874 36.1389817 0 EGADS : 17 Yes 123.552357 97.6729236 4.7180639 EGADS : 18 Yes 118.391317 97.6729236 3.99272703 EGADS : 19 Yes 0 0 1947.05079 EGADS : 20 Yes 0 0 0 EGADS : 21 Yes 0 1953.45847 1947.05079 EGADS : 22 Yes 0 1953.45847 0 EGADS : 23 Yes 2040.21562 0 1947.05079 EGADS : 24 Yes 2040.21562 0 0 EGADS : 25 Yes 2040.21562 1953.45847 1947.05079 EGADS : 26 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 22.2515 AFLR4 : Reference Length = 22.2515 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 428.344 AFLR4 : Abs Min Surf Spacing = 0.0556287 AFLR4 : Min Surf Spacing = 0.111257 AFLR4 : Max Surf Spacing = 2.22515 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD AFLR4 : 2 CAD geometry 0 STD AFLR4 : 3 CAD geometry 0 STD AFLR4 : 4 CAD geometry 0 STD AFLR4 : 5 CAD geometry 0 STD AFLR4 : 6 CAD geometry 0 STD AFLR4 : 7 CAD geometry 0 STD AFLR4 : 8 CAD geometry 0 STD AFLR4 : 9 CAD geometry 0 STD AFLR4 : 10 CAD geometry 0 STD AFLR4 : 11 CAD geometry 0 STD AFLR4 : 12 CAD geometry 0 STD AFLR4 : 13 CAD geometry 0 STD AFLR4 : 14 CAD geometry 0 STD AFLR4 : 15 CAD geometry 0 STD AFLR4 : 16 CAD geometry 0 STD AFLR4 : 17 CAD geometry 0 STD AFLR4 : 18 CAD geometry 0 STD AFLR4 : 19 CAD geometry 0 FARFIELD AFLR4 : 20 CAD geometry 0 FARFIELD AFLR4 : 21 CAD geometry 0 FARFIELD AFLR4 : 22 CAD geometry 0 FARFIELD AFLR4 : 23 CAD geometry 0 FARFIELD AFLR4 : 24 CAD geometry 0 FARFIELD AFLR4 : Case has 2 Proximity Checking Components AFLR4 : Component 1 includes Definitions 9 10 11 12 13 14 15 16 17 18 AFLR4 : Component 2 includes Definitions 1 2 3 4 5 6 7 8 AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Define CAD surface definition 17 AFLR4 : Define CAD surface definition 18 AFLR4 : Define CAD surface definition 19 AFLR4 : Define CAD surface definition 20 AFLR4 : Define CAD surface definition 21 AFLR4 : Define CAD surface definition 22 AFLR4 : Define CAD surface definition 23 AFLR4 : Define CAD surface definition 24 AFLR43 : INPUT SURFACE MESH FROM TESS AFLR43 : Quad Surface Faces= 0 AFLR43 : Tria Surface Faces= 191072 AFLR43 : Nodes = 95540 UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR3 : --------------------------------------- AFLR3 : AFLR3 LIBRARY AFLR3 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR3 : TETRAHEDRAL GRID GENERATOR AFLR3 : Version Number 16.32.50 AFLR3 : Version Date 10/31/23 @ 06:31PM AFLR3 : Compile OS Darwin 22.6.0 x86_64 AFLR3 : Compile Date 11/01/23 @ 12:19PM AFLR3 : Copyright 1994-2021, D.L. Marcum AFLR3 : --------------------------------------- AFLR3 IC : INPUT SURFACE GRID CHECK AFLR3 IC : Nodes, Elements = 95540 0 UG3 : Boundary Conditions UG3 : B-Face ID Boundary Condition UG3 : 1 Solid UG3 : 2 Solid UG3 : 3 Solid UG3 : 4 Solid UG3 : 5 Solid UG3 : 6 Solid UG3 : 7 Solid UG3 : 8 Solid UG3 : 9 Solid UG3 : 10 Solid UG3 : 11 Solid UG3 : 12 Solid UG3 : 13 Solid UG3 : 14 Solid UG3 : 15 Solid UG3 : 16 Solid UG3 : 17 Solid UG3 : 18 Solid UG3 : 19 FarField UG3 : 20 FarField UG3 : 21 FarField UG3 : 22 FarField UG3 : 23 FarField UG3 : 24 FarField AFLR3 : CPU Time = 0.351 seconds AFLR3 IG : INITIAL VOLUME GRID GENERATION AFLR3 IG : Nodes, Elements = 95540 0 AFLR3 IG : Nodes, Elements = 8 10 AFLR3 IG : Nodes, Elements = 19110 113248 AFLR3 IG : Nodes, Elements = 38220 247440 AFLR3 IG : Nodes, Elements = 57330 367745 AFLR3 IG : Nodes, Elements = 76440 520135 AFLR3 IG : Nodes, Elements = 95547 672875 AFLR3 IG : Nodes, Elements = 95547 671480 AFLR3 IG : Nodes, Elements = 95547 671533 AFLR3 IG : Nodes, Elements = 95547 671402 AFLR3 IG : Nodes, Elements = 95540 378462 AFLR3 IG : Nodes, Elements = 95540 378726 AFLR3 IG : Nodes, Elements = 95540 305842 AFLR3 IG : Nodes, Elements = 95540 287127 AFLR3 : CPU Time = 11.548 seconds AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION AFLR3 GG : Nodes, Elements = 95540 287127 AFLR3 GGi: Nodes, Elements = 95541 287130 AFLR3 GGi: Nodes, Elements = 95541 287141 AFLR3 GGi: Nodes, Elements = 95541 287142 AFLR3 GGi: Nodes, Elements = 95543 287148 AFLR3 GGi: Nodes, Elements = 95543 287205 AFLR3 GGi: Nodes, Elements = 95543 287228 AFLR3 GG : Nodes, Elements = 136408 410551 AFLR3 GG : Nodes, Elements = 136408 573470 AFLR3 GG : Nodes, Elements = 136408 533381 AFLR3 GG : Nodes, Elements = 170819 637623 AFLR3 GG : Nodes, Elements = 170819 773192 AFLR3 GG : Nodes, Elements = 170819 731565 AFLR3 GG : Nodes, Elements = 206009 837914 AFLR3 GG : Nodes, Elements = 206009 978011 AFLR3 GG : Nodes, Elements = 206009 935997 AFLR3 GG : Nodes, Elements = 241032 1041536 AFLR3 GG : Nodes, Elements = 241032 1184601 AFLR3 GG : Nodes, Elements = 241032 1144028 AFLR3 GG : Nodes, Elements = 276099 1249644 AFLR3 GG : Nodes, Elements = 276099 1388535 AFLR3 GG : Nodes, Elements = 276099 1350967 AFLR3 GG : Nodes, Elements = 310846 1455570 AFLR3 GG : Nodes, Elements = 310846 1593212 AFLR3 GG : Nodes, Elements = 310846 1556216 AFLR3 GG : Nodes, Elements = 345374 1660116 AFLR3 GG : Nodes, Elements = 345374 1796669 AFLR3 GG : Nodes, Elements = 345374 1760788 AFLR3 GG : Nodes, Elements = 378925 1861761 AFLR3 GG : Nodes, Elements = 378925 1993110 AFLR3 GG : Nodes, Elements = 378925 1960169 AFLR3 GG : Nodes, Elements = 411461 2058056 AFLR3 GG : Nodes, Elements = 411461 2184587 AFLR3 GG : Nodes, Elements = 411461 2152891 AFLR3 GG : Nodes, Elements = 443112 2248182 AFLR3 GG : Nodes, Elements = 443112 2371784 AFLR3 GG : Nodes, Elements = 443112 2340710 AFLR3 GG : Nodes, Elements = 473548 2432312 AFLR3 GG : Nodes, Elements = 473548 2552093 AFLR3 GG : Nodes, Elements = 473548 2521057 AFLR3 GG : Nodes, Elements = 502892 2609389 AFLR3 GG : Nodes, Elements = 502892 2724830 AFLR3 GG : Nodes, Elements = 502892 2695426 AFLR3 GG : Nodes, Elements = 531293 2780879 AFLR3 GG : Nodes, Elements = 531293 2892730 AFLR3 GG : Nodes, Elements = 531293 2864350 AFLR3 GG : Nodes, Elements = 558794 2947116 AFLR3 GG : Nodes, Elements = 558794 3053977 AFLR3 GG : Nodes, Elements = 558794 3027479 AFLR3 GG : Nodes, Elements = 585079 3106574 AFLR3 GG : Nodes, Elements = 585079 3208642 AFLR3 GG : Nodes, Elements = 585079 3183527 AFLR3 GG : Nodes, Elements = 610505 3260009 AFLR3 GG : Nodes, Elements = 610505 3358804 AFLR3 GG : Nodes, Elements = 610505 3334322 AFLR3 GG : Nodes, Elements = 635099 3408333 AFLR3 GG : Nodes, Elements = 635099 3504302 AFLR3 GG : Nodes, Elements = 635099 3480288 AFLR3 GG : Nodes, Elements = 658851 3551719 AFLR3 GG : Nodes, Elements = 658851 3643539 AFLR3 GG : Nodes, Elements = 658851 3621028 AFLR3 GG : Nodes, Elements = 681666 3689667 AFLR3 GG : Nodes, Elements = 681666 3778766 AFLR3 GG : Nodes, Elements = 681666 3756529 AFLR3 GG : Nodes, Elements = 703837 3823217 AFLR3 GG : Nodes, Elements = 703837 3909372 AFLR3 GG : Nodes, Elements = 703837 3887888 AFLR3 GG : Nodes, Elements = 725158 3951988 AFLR3 GG : Nodes, Elements = 725158 4034454 AFLR3 GG : Nodes, Elements = 725158 4014246 AFLR3 GG : Nodes, Elements = 745652 4075851 AFLR3 GG : Nodes, Elements = 745652 4155349 AFLR3 GG : Nodes, Elements = 745652 4135924 AFLR3 GG : Nodes, Elements = 765434 4195370 AFLR3 GG : Nodes, Elements = 765434 4271915 AFLR3 GG : Nodes, Elements = 765434 4252991 AFLR3 GG : Nodes, Elements = 784582 4310530 AFLR3 GG : Nodes, Elements = 784582 4385833 AFLR3 GG : Nodes, Elements = 784582 4366802 AFLR3 GG : Nodes, Elements = 803082 4422397 AFLR3 GG : Nodes, Elements = 803082 4494089 AFLR3 GG : Nodes, Elements = 803082 4476525 AFLR3 GG : Nodes, Elements = 820791 4529733 AFLR3 GG : Nodes, Elements = 820791 4598745 AFLR3 GG : Nodes, Elements = 820791 4581657 AFLR3 GG : Nodes, Elements = 837830 4632848 AFLR3 GG : Nodes, Elements = 837830 4699294 AFLR3 GG : Nodes, Elements = 837830 4682938 AFLR3 GG : Nodes, Elements = 854503 4733003 AFLR3 GG : Nodes, Elements = 854503 4797490 AFLR3 GG : Nodes, Elements = 854503 4781899 AFLR3 GG : Nodes, Elements = 870424 4829702 AFLR3 GG : Nodes, Elements = 870424 4891624 AFLR3 GG : Nodes, Elements = 870424 4876102 AFLR3 GG : Nodes, Elements = 885805 4922291 AFLR3 GG : Nodes, Elements = 885805 4981472 AFLR3 GG : Nodes, Elements = 885805 4967212 AFLR3 GG : Nodes, Elements = 900588 5011608 AFLR3 GG : Nodes, Elements = 900588 5068491 AFLR3 GG : Nodes, Elements = 900588 5054733 AFLR3 GG : Nodes, Elements = 914877 5097644 AFLR3 GG : Nodes, Elements = 914877 5153115 AFLR3 GG : Nodes, Elements = 914877 5139221 AFLR3 GG : Nodes, Elements = 928570 5180323 AFLR3 GG : Nodes, Elements = 928570 5233321 AFLR3 GG : Nodes, Elements = 928570 5220381 AFLR3 GG : Nodes, Elements = 941719 5259855 AFLR3 GG : Nodes, Elements = 941719 5310534 AFLR3 GG : Nodes, Elements = 941719 5298325 AFLR3 GG : Nodes, Elements = 954683 5337236 AFLR3 GG : Nodes, Elements = 954683 5386713 AFLR3 GG : Nodes, Elements = 954683 5374852 AFLR3 GG : Nodes, Elements = 967367 5412930 AFLR3 GG : Nodes, Elements = 967367 5462247 AFLR3 GG : Nodes, Elements = 967367 5449893 AFLR3 GG : Nodes, Elements = 979708 5486924 AFLR3 GG : Nodes, Elements = 979708 5534306 AFLR3 GG : Nodes, Elements = 979708 5522874 AFLR3 GG : Nodes, Elements = 991642 5558690 AFLR3 GG : Nodes, Elements = 991642 5604904 AFLR3 GG : Nodes, Elements = 991642 5593457 AFLR3 GG : Nodes, Elements = 1003166 5628042 AFLR3 GG : Nodes, Elements = 1003166 5672643 AFLR3 GG : Nodes, Elements = 1003166 5661590 AFLR3 GG : Nodes, Elements = 1014374 5695225 AFLR3 GG : Nodes, Elements = 1014374 5738236 AFLR3 GG : Nodes, Elements = 1014374 5727866 AFLR3 GG : Nodes, Elements = 1025085 5760010 AFLR3 GG : Nodes, Elements = 1025085 5801881 AFLR3 GG : Nodes, Elements = 1025085 5791266 AFLR3 GG : Nodes, Elements = 1035336 5822028 AFLR3 GG : Nodes, Elements = 1035336 5861295 AFLR3 GG : Nodes, Elements = 1035336 5851793 AFLR3 GG : Nodes, Elements = 1044896 5880484 AFLR3 GG : Nodes, Elements = 1044896 5917028 AFLR3 GG : Nodes, Elements = 1044896 5908078 AFLR3 GG : Nodes, Elements = 1053896 5935090 AFLR3 GG : Nodes, Elements = 1053896 5969750 AFLR3 GG : Nodes, Elements = 1053896 5961217 AFLR3 GG : Nodes, Elements = 1062332 5986533 AFLR3 GG : Nodes, Elements = 1062332 6018832 AFLR3 GG : Nodes, Elements = 1062332 6010896 AFLR3 GG : Nodes, Elements = 1070082 6034154 AFLR3 GG : Nodes, Elements = 1070082 6064554 AFLR3 GG : Nodes, Elements = 1070082 6056725 AFLR3 GG : Nodes, Elements = 1077317 6078438 AFLR3 GG : Nodes, Elements = 1077317 6106556 AFLR3 GG : Nodes, Elements = 1077317 6099606 AFLR3 GG : Nodes, Elements = 1083710 6118792 AFLR3 GG : Nodes, Elements = 1083710 6143419 AFLR3 GG : Nodes, Elements = 1083710 6137175 AFLR3 GG : Nodes, Elements = 1089155 6153515 AFLR3 GG : Nodes, Elements = 1089155 6175097 AFLR3 GG : Nodes, Elements = 1089155 6169409 AFLR3 GG : Nodes, Elements = 1093772 6183263 AFLR3 GG : Nodes, Elements = 1093772 6201287 AFLR3 GG : Nodes, Elements = 1093772 6196612 AFLR3 GG : Nodes, Elements = 1097610 6208130 AFLR3 GG : Nodes, Elements = 1097610 6223008 AFLR3 GG : Nodes, Elements = 1097610 6219256 AFLR3 GG : Nodes, Elements = 1100610 6228262 AFLR3 GG : Nodes, Elements = 1100610 6240091 AFLR3 GG : Nodes, Elements = 1100610 6236944 AFLR3 GG : Nodes, Elements = 1102997 6244110 AFLR3 GG : Nodes, Elements = 1102997 6253372 AFLR3 GG : Nodes, Elements = 1102997 6250910 AFLR3 GG : Nodes, Elements = 1104853 6256478 AFLR3 GG : Nodes, Elements = 1104853 6263639 AFLR3 GG : Nodes, Elements = 1104853 6261816 AFLR3 GG : Nodes, Elements = 1106240 6265978 AFLR3 GG : Nodes, Elements = 1106240 6271482 AFLR3 GG : Nodes, Elements = 1106240 6269937 AFLR3 GG : Nodes, Elements = 1107246 6272959 AFLR3 GG : Nodes, Elements = 1107246 6276904 AFLR3 GG : Nodes, Elements = 1107246 6275810 AFLR3 GG : Nodes, Elements = 1107939 6277890 AFLR3 GG : Nodes, Elements = 1107939 6280627 AFLR3 GG : Nodes, Elements = 1107939 6279853 AFLR3 GG : Nodes, Elements = 1108430 6281327 AFLR3 GG : Nodes, Elements = 1108430 6283334 AFLR3 GG : Nodes, Elements = 1108430 6282741 AFLR3 GG : Nodes, Elements = 1108784 6283803 AFLR3 GG : Nodes, Elements = 1108784 6285169 AFLR3 GG : Nodes, Elements = 1108784 6284800 AFLR3 GG : Nodes, Elements = 1108996 6285436 AFLR3 GG : Nodes, Elements = 1108996 6286284 AFLR3 GG : Nodes, Elements = 1108996 6286027 AFLR3 GG : Nodes, Elements = 1109132 6286435 AFLR3 GG : Nodes, Elements = 1109132 6287005 AFLR3 GG : Nodes, Elements = 1109132 6286813 AFLR3 GG : Nodes, Elements = 1109190 6286987 AFLR3 GG : Nodes, Elements = 1109190 6287235 AFLR3 GG : Nodes, Elements = 1109190 6287150 AFLR3 GG : Nodes, Elements = 1109219 6287237 AFLR3 GG : Nodes, Elements = 1109219 6287363 AFLR3 GG : Nodes, Elements = 1109219 6287320 AFLR3 GG : Nodes, Elements = 1109229 6287350 AFLR3 GG : Nodes, Elements = 1109229 6287394 AFLR3 GG : Nodes, Elements = 1109229 6287375 AFLR3 GG : Nodes, Elements = 1109233 6287387 AFLR3 GG : Nodes, Elements = 1109233 6287402 AFLR3 GG : Nodes, Elements = 1109233 6287398 AFLR3 GG : Nodes, Elements = 1109328 6287683 AFLR3 GG : Nodes, Elements = 1109328 6288208 AFLR3 GG : Nodes, Elements = 1109328 6287904 AFLR3 GG : Nodes, Elements = 1109355 6287985 AFLR3 GG : Nodes, Elements = 1109355 6288087 AFLR3 GG : Nodes, Elements = 1109355 6288056 AFLR3 GG : Nodes, Elements = 1109359 6288068 AFLR3 GG : Nodes, Elements = 1109359 6288082 AFLR3 GG : Nodes, Elements = 1109359 6288078 AFLR3 GG : Nodes, Elements = 1109360 6288081 AFLR3 GG : Nodes, Elements = 1109360 6288086 AFLR3 GG : Nodes, Elements = 1109360 6288084 AFLR3 GG : Nodes, Elements = 1109361 6288087 AFLR3 GG : Nodes, Elements = 1109361 6288090 AFLR3 GG : Nodes, Elements = 1109361 6288089 AFLR3 : CPU Time = 3.402 minutes AFLR3 QI : QUALITY IMPROVEMENT AFLR3 QI : Nodes, Elements = 1109361 6288089 AFLR3 QI : Nodes, Elements = 1104673 6261692 AFLR3 QI : Nodes, Elements = 1103868 6257089 AFLR3 QI : Nodes, Elements = 1103699 6256141 AFLR3 QI : Nodes, Elements = 1103677 6256025 AFLR3 QI : Nodes, Elements = 1103674 6256006 AFLR3 QI : Nodes, Elements = 1103674 6278209 AFLR3 QI : Nodes, Elements = 1103674 6255082 AFLR3 QI : Nodes, Elements = 1103674 6244296 AFLR3 QI : Nodes, Elements = 1103674 6246194 AFLR3 QI : Nodes, Elements = 1103674 6242316 AFLR3 QI : Nodes, Elements = 1103674 6241086 AFLR3 QI : Nodes, Elements = 1103674 6242231 AFLR3 QI : Nodes, Elements = 1103674 6240808 AFLR3 QI : Nodes, Elements = 1103674 6240349 AFLR3 QI : Nodes, Elements = 1103674 6241362 AFLR3 QI : Nodes, Elements = 1103674 6240249 AFLR3 QI : Nodes, Elements = 1103674 6239992 AFLR3 QI : Nodes, Elements = 1103674 6240962 AFLR3 QI : Nodes, Elements = 1103674 6239957 AFLR3 QI : Nodes, Elements = 1103674 6239826 AFLR3 : CPU Time = 55.823 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 6239826 UG3 : Min, Max Ang = 5.227 161.3 UG3 : Average Angle = 70.2 UG3 : No. Angle>160.0 = 2 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 6239826 UG3 : Min Vol = 1.65e-05 UG3 : Average Vol = 9.56e+03 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol160.0 = 2 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 6239826 UG3 : Min Vol = 1.65e-05 UG3 : Average Vol = 9.56e+03 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol160.0 = 32 UG3 : No. Angle>179.9 = 1 UG3 : No. Pyramid Elems = 147 UG3 : Min, Max Ang = 8.861 172.3 UG3 : Average Angle = 80.9 UG3 : No. Angle>160.0 = 12 UG3 : No. Angle>179.9 = 0 UG3 : No. Prism Elems = 156367 UG3 : Min, Max Ang = 9.482 174.2 UG3 : Average Angle = 80 UG3 : No. Angle>160.0 = 421 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 423573 UG3 : Min Vol = 8.4e-05 UG3 : Average Vol = 1.41e+05 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol160.0 = 290 UG3 : No. Angle>179.9 = 0 UG3 : No. Pyramid Elems = 2793 UG3 : Min, Max Ang = 7.032 171.7 UG3 : Average Angle = 82.6 UG3 : No. Angle>160.0 = 56 UG3 : No. Angle>179.9 = 0 UG3 : No. Prism Elems = 104033 UG3 : Min, Max Ang = 6.792 174.6 UG3 : Average Angle = 80.1 UG3 : No. Angle>160.0 = 561 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 318666 UG3 : Min Vol = 0.000481 UG3 : Average Vol = 1.87e+05 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol160.0 = 346 UG3 : No. Angle>179.9 = 0 UG3 : No. Pyramid Elems = 20660 UG3 : Min, Max Ang = 7.23 174.4 UG3 : Average Angle = 82.6 UG3 : No. Angle>160.0 = 128 UG3 : No. Angle>179.9 = 0 UG3 : No. Prism Elems = 390906 UG3 : Min, Max Ang = 6.851 174.6 UG3 : Average Angle = 80.1 UG3 : No. Angle>160.0 = 732 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 1453193 UG3 : Min Vol = 8.19e-06 UG3 : Average Vol = 4.1e+04 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol Toal Elements 71596 real 0m26.201s user 0m27.113s sys 0m4.550s + status=0 + set +x ================================================= solutions/session07/aflr4_InviscidTransport_150k.py passed (as expected) ================================================= ================================================= 2_su2_InviscidWing.py test; + python 2_su2_InviscidWing.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - leftWing Mesh sizing name - riteWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 1 1 2 3 6 EGADS : 2 Yes 0 0 1 1 1 1 4 5 EGADS : 3 Yes 0 0 1 1 1 1 4 8 EGADS : 4 Yes 0 0 1 1 1 2 3 5 EGADS : 5 Yes 0 0 1 1 1 2 4 EGADS : 6 Yes 0 0 1 1 1 1 7 8 EGADS : 7 Yes 0 0 1 1 1 6 9 10 EGADS : 8 Yes 0 0 1 1 1 3 6 9 EGADS : 9 Yes 0 0 1 1 1 7 8 10 EGADS : 10 Yes 0 0 1 1 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 2651.51 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 5 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1107 2082 0 AFLR4 : Nodes, Trias,Quads= 685 1238 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1473 2759 0 AFLR4 : Nodes, Trias,Quads= 721 1255 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 1116 2100 0 AFLR4 : Nodes, Trias,Quads= 671 1210 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1458 2729 0 AFLR4 : Nodes, Trias,Quads= 714 1241 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 20 24 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1108 2084 0 AFLR4 : Nodes, Trias,Quads= 683 1234 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 1488 2789 0 AFLR4 : Nodes, Trias,Quads= 714 1241 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 1112 2092 0 AFLR4 : Nodes, Trias,Quads= 653 1174 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 1456 2725 0 AFLR4 : Nodes, Trias,Quads= 708 1229 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 20 24 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 4933 9858 1312 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 4933 9858 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 12796 24695 0 AFLR4 : Nodes, Trias,Quads= 7764 14631 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 29245 57075 0 AFLR4 : Nodes, Trias,Quads= 12448 23481 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 12136 23411 0 AFLR4 : Nodes, Trias,Quads= 7447 14033 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 29424 57435 0 AFLR4 : Nodes, Trias,Quads= 12399 23385 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 196 293 0 AFLR4 : Nodes, Trias,Quads= 188 277 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 12819 24741 0 AFLR4 : Nodes, Trias,Quads= 7725 14553 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 29449 57483 0 AFLR4 : Nodes, Trias,Quads= 12413 23411 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 12144 23427 0 AFLR4 : Nodes, Trias,Quads= 7471 14081 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 29445 57477 0 AFLR4 : Nodes, Trias,Quads= 12478 23543 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 196 293 0 AFLR4 : Nodes, Trias,Quads= 188 277 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 75858 151708 9398 OVERALL : CPU Time = 3.002 seconds Body 1 (of 2) Number of nodes = 75838 Number of elements = 151672 Number of triangle elements = 151672 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 20 Number of elements = 36 Number of triangle elements = 36 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 75858 Total number of elements = 151708 Total number of triangle elements = 151708 Total number of quadrilateral elements = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Getting volume mesh UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 1 1 2 3 6 EGADS : 2 Yes 0 0 1 1 1 1 4 5 EGADS : 3 Yes 0 0 1 1 1 1 4 8 EGADS : 4 Yes 0 0 1 1 1 2 3 5 EGADS : 5 Yes 0 0 1 1 1 2 4 EGADS : 6 Yes 0 0 1 1 1 1 7 8 EGADS : 7 Yes 0 0 1 1 1 6 9 10 EGADS : 8 Yes 0 0 1 1 1 3 6 9 EGADS : 9 Yes 0 0 1 1 1 7 8 10 EGADS : 10 Yes 0 0 1 1 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 13.1976 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 428.309 AFLR4 : Abs Min Surf Spacing = 0.032994 AFLR4 : Min Surf Spacing = 0.065988 AFLR4 : Max Surf Spacing = 1.31976 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD AFLR4 : 2 CAD geometry 0 STD AFLR4 : 3 CAD geometry 0 STD AFLR4 : 4 CAD geometry 0 STD AFLR4 : 5 CAD geometry 0 STD AFLR4 : 6 CAD geometry 0 STD AFLR4 : 7 CAD geometry 0 STD AFLR4 : 8 CAD geometry 0 STD AFLR4 : 9 CAD geometry 0 STD AFLR4 : 10 CAD geometry 0 STD AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR43 : INPUT SURFACE MESH FROM TESS AFLR43 : Quad Surface Faces= 0 AFLR43 : Tria Surface Faces= 151708 AFLR43 : Nodes = 75858 UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR3 : --------------------------------------- AFLR3 : AFLR3 LIBRARY AFLR3 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR3 : TETRAHEDRAL GRID GENERATOR AFLR3 : Version Number 16.32.50 AFLR3 : Version Date 10/31/23 @ 06:31PM AFLR3 : Compile OS Darwin 22.6.0 x86_64 AFLR3 : Compile Date 11/01/23 @ 12:19PM AFLR3 : Copyright 1994-2021, D.L. Marcum AFLR3 : --------------------------------------- AFLR3 IC : INPUT SURFACE GRID CHECK AFLR3 IC : Nodes, Elements = 75858 0 UG3 : Boundary Conditions UG3 : B-Face ID Boundary Condition UG3 : 1 Solid UG3 : 2 Solid UG3 : 3 Solid UG3 : 4 Solid UG3 : 5 Solid UG3 : 6 Solid UG3 : 7 Solid UG3 : 8 Solid UG3 : 9 Solid UG3 : 10 Solid UG3 : 11 FarField UG3 : 12 FarField UG3 : 13 FarField UG3 : 14 FarField UG3 : 15 FarField UG3 : 16 FarField AFLR3 : CPU Time = 0.250 seconds AFLR3 IG : INITIAL VOLUME GRID GENERATION AFLR3 IG : Nodes, Elements = 75858 0 AFLR3 IG : Nodes, Elements = 8 10 AFLR3 IG : Nodes, Elements = 15174 110930 AFLR3 IG : Nodes, Elements = 30348 239512 AFLR3 IG : Nodes, Elements = 45522 364376 AFLR3 IG : Nodes, Elements = 60696 488708 AFLR3 IG : Nodes, Elements = 75865 649511 AFLR3 IG : Nodes, Elements = 75865 648308 AFLR3 IG : Nodes, Elements = 75865 648424 AFLR3 IG : Nodes, Elements = 75865 647472 AFLR3 IG : Nodes, Elements = 75858 416319 AFLR3 IG : Nodes, Elements = 75858 417620 AFLR3 IG : Nodes, Elements = 75858 262267 AFLR3 IG : Nodes, Elements = 75858 238929 AFLR3 : CPU Time = 9.489 seconds AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION AFLR3 GG : Nodes, Elements = 75858 238929 AFLR3 GG : Nodes, Elements = 97121 303288 AFLR3 GG : Nodes, Elements = 97121 384995 AFLR3 GG : Nodes, Elements = 97121 351355 AFLR3 GG : Nodes, Elements = 114881 407778 AFLR3 GG : Nodes, Elements = 114881 484750 AFLR3 GG : Nodes, Elements = 114881 454637 AFLR3 GG : Nodes, Elements = 138960 529123 AFLR3 GG : Nodes, Elements = 138960 631021 AFLR3 GG : Nodes, Elements = 138960 592337 AFLR3 GG : Nodes, Elements = 164714 671223 AFLR3 GG : Nodes, Elements = 164714 782517 AFLR3 GG : Nodes, Elements = 164714 744165 AFLR3 GG : Nodes, Elements = 193389 831240 AFLR3 GG : Nodes, Elements = 193389 952591 AFLR3 GG : Nodes, Elements = 193389 915788 AFLR3 GG : Nodes, Elements = 223793 1007653 AFLR3 GG : Nodes, Elements = 223793 1131220 AFLR3 GG : Nodes, Elements = 223793 1095610 AFLR3 GG : Nodes, Elements = 254697 1188716 AFLR3 GG : Nodes, Elements = 254697 1312627 AFLR3 GG : Nodes, Elements = 254697 1278678 AFLR3 GG : Nodes, Elements = 285123 1370225 AFLR3 GG : Nodes, Elements = 285123 1492164 AFLR3 GG : Nodes, Elements = 285123 1459185 AFLR3 GG : Nodes, Elements = 314749 1548281 AFLR3 GG : Nodes, Elements = 314749 1666496 AFLR3 GG : Nodes, Elements = 314749 1635328 AFLR3 GG : Nodes, Elements = 343185 1720784 AFLR3 GG : Nodes, Elements = 343185 1834449 AFLR3 GG : Nodes, Elements = 343185 1804754 AFLR3 GG : Nodes, Elements = 370197 1885926 AFLR3 GG : Nodes, Elements = 370197 1992358 AFLR3 GG : Nodes, Elements = 370197 1965216 AFLR3 GG : Nodes, Elements = 395625 2041613 AFLR3 GG : Nodes, Elements = 395625 2142093 AFLR3 GG : Nodes, Elements = 395625 2116556 AFLR3 GG : Nodes, Elements = 419704 2188894 AFLR3 GG : Nodes, Elements = 419704 2283914 AFLR3 GG : Nodes, Elements = 419704 2259708 AFLR3 GG : Nodes, Elements = 442391 2327833 AFLR3 GG : Nodes, Elements = 442391 2417661 AFLR3 GG : Nodes, Elements = 442391 2394642 AFLR3 GG : Nodes, Elements = 463683 2458572 AFLR3 GG : Nodes, Elements = 463683 2543123 AFLR3 GG : Nodes, Elements = 463683 2521112 AFLR3 GG : Nodes, Elements = 483827 2581588 AFLR3 GG : Nodes, Elements = 483827 2661051 AFLR3 GG : Nodes, Elements = 483827 2640939 AFLR3 GG : Nodes, Elements = 502669 2697501 AFLR3 GG : Nodes, Elements = 502669 2770894 AFLR3 GG : Nodes, Elements = 502669 2752651 AFLR3 GG : Nodes, Elements = 520300 2805580 AFLR3 GG : Nodes, Elements = 520300 2874408 AFLR3 GG : Nodes, Elements = 520300 2857298 AFLR3 GG : Nodes, Elements = 536675 2906461 AFLR3 GG : Nodes, Elements = 536675 2970904 AFLR3 GG : Nodes, Elements = 536675 2954392 AFLR3 GG : Nodes, Elements = 551844 2999934 AFLR3 GG : Nodes, Elements = 551844 3060132 AFLR3 GG : Nodes, Elements = 551844 3044500 AFLR3 GG : Nodes, Elements = 565681 3086032 AFLR3 GG : Nodes, Elements = 565681 3140377 AFLR3 GG : Nodes, Elements = 565681 3126467 AFLR3 GG : Nodes, Elements = 578520 3165000 AFLR3 GG : Nodes, Elements = 578520 3215601 AFLR3 GG : Nodes, Elements = 578520 3202688 AFLR3 GG : Nodes, Elements = 590236 3237862 AFLR3 GG : Nodes, Elements = 590236 3283447 AFLR3 GG : Nodes, Elements = 590236 3272024 AFLR3 GG : Nodes, Elements = 600891 3304007 AFLR3 GG : Nodes, Elements = 600891 3345640 AFLR3 GG : Nodes, Elements = 600891 3335099 AFLR3 GG : Nodes, Elements = 610653 3364398 AFLR3 GG : Nodes, Elements = 610653 3402538 AFLR3 GG : Nodes, Elements = 610653 3392929 AFLR3 GG : Nodes, Elements = 619681 3420022 AFLR3 GG : Nodes, Elements = 619681 3455219 AFLR3 GG : Nodes, Elements = 619681 3446093 AFLR3 GG : Nodes, Elements = 628219 3471726 AFLR3 GG : Nodes, Elements = 628219 3505699 AFLR3 GG : Nodes, Elements = 628219 3496844 AFLR3 GG : Nodes, Elements = 636038 3520308 AFLR3 GG : Nodes, Elements = 636038 3551135 AFLR3 GG : Nodes, Elements = 636038 3543045 AFLR3 GG : Nodes, Elements = 643376 3565069 AFLR3 GG : Nodes, Elements = 643376 3593962 AFLR3 GG : Nodes, Elements = 643376 3586413 AFLR3 GG : Nodes, Elements = 650191 3606868 AFLR3 GG : Nodes, Elements = 650191 3633632 AFLR3 GG : Nodes, Elements = 650191 3626847 AFLR3 GG : Nodes, Elements = 656508 3645807 AFLR3 GG : Nodes, Elements = 656508 3670861 AFLR3 GG : Nodes, Elements = 656508 3664202 AFLR3 GG : Nodes, Elements = 662433 3681982 AFLR3 GG : Nodes, Elements = 662433 3705355 AFLR3 GG : Nodes, Elements = 662433 3699226 AFLR3 GG : Nodes, Elements = 667990 3715904 AFLR3 GG : Nodes, Elements = 667990 3737646 AFLR3 GG : Nodes, Elements = 667990 3731986 AFLR3 GG : Nodes, Elements = 673254 3747784 AFLR3 GG : Nodes, Elements = 673254 3768503 AFLR3 GG : Nodes, Elements = 673254 3763031 AFLR3 GG : Nodes, Elements = 678157 3777746 AFLR3 GG : Nodes, Elements = 678157 3796918 AFLR3 GG : Nodes, Elements = 678157 3791911 AFLR3 GG : Nodes, Elements = 682710 3805572 AFLR3 GG : Nodes, Elements = 682710 3823091 AFLR3 GG : Nodes, Elements = 682710 3818679 AFLR3 GG : Nodes, Elements = 686953 3831414 AFLR3 GG : Nodes, Elements = 686953 3848097 AFLR3 GG : Nodes, Elements = 686953 3843660 AFLR3 GG : Nodes, Elements = 690854 3855370 AFLR3 GG : Nodes, Elements = 690854 3870670 AFLR3 GG : Nodes, Elements = 690854 3866655 AFLR3 GG : Nodes, Elements = 694460 3877474 AFLR3 GG : Nodes, Elements = 694460 3891624 AFLR3 GG : Nodes, Elements = 694460 3887901 AFLR3 GG : Nodes, Elements = 697850 3898077 AFLR3 GG : Nodes, Elements = 697850 3911030 AFLR3 GG : Nodes, Elements = 697850 3907854 AFLR3 GG : Nodes, Elements = 700996 3917295 AFLR3 GG : Nodes, Elements = 700996 3929596 AFLR3 GG : Nodes, Elements = 700996 3926327 AFLR3 GG : Nodes, Elements = 703836 3934850 AFLR3 GG : Nodes, Elements = 703836 3945999 AFLR3 GG : Nodes, Elements = 703836 3942976 AFLR3 GG : Nodes, Elements = 706440 3950791 AFLR3 GG : Nodes, Elements = 706440 3961150 AFLR3 GG : Nodes, Elements = 706440 3958314 AFLR3 GG : Nodes, Elements = 708730 3965187 AFLR3 GG : Nodes, Elements = 708730 3974144 AFLR3 GG : Nodes, Elements = 708730 3971783 AFLR3 GG : Nodes, Elements = 710708 3977720 AFLR3 GG : Nodes, Elements = 710708 3985328 AFLR3 GG : Nodes, Elements = 710708 3983276 AFLR3 GG : Nodes, Elements = 712424 3988426 AFLR3 GG : Nodes, Elements = 712424 3995075 AFLR3 GG : Nodes, Elements = 712424 3993284 AFLR3 GG : Nodes, Elements = 713833 3997513 AFLR3 GG : Nodes, Elements = 713833 4003187 AFLR3 GG : Nodes, Elements = 713833 4001605 AFLR3 GG : Nodes, Elements = 715022 4005173 AFLR3 GG : Nodes, Elements = 715022 4009923 AFLR3 GG : Nodes, Elements = 715022 4008585 AFLR3 GG : Nodes, Elements = 715991 4011493 AFLR3 GG : Nodes, Elements = 715991 4015396 AFLR3 GG : Nodes, Elements = 715991 4014283 AFLR3 GG : Nodes, Elements = 716774 4016634 AFLR3 GG : Nodes, Elements = 716774 4019712 AFLR3 GG : Nodes, Elements = 716774 4018875 AFLR3 GG : Nodes, Elements = 717387 4020715 AFLR3 GG : Nodes, Elements = 717387 4023245 AFLR3 GG : Nodes, Elements = 717387 4022493 AFLR3 GG : Nodes, Elements = 717893 4024011 AFLR3 GG : Nodes, Elements = 717893 4025943 AFLR3 GG : Nodes, Elements = 717893 4025436 AFLR3 GG : Nodes, Elements = 718259 4026534 AFLR3 GG : Nodes, Elements = 718259 4027955 AFLR3 GG : Nodes, Elements = 718259 4027575 AFLR3 GG : Nodes, Elements = 718519 4028355 AFLR3 GG : Nodes, Elements = 718519 4029402 AFLR3 GG : Nodes, Elements = 718519 4029087 AFLR3 GG : Nodes, Elements = 718704 4029642 AFLR3 GG : Nodes, Elements = 718704 4030385 AFLR3 GG : Nodes, Elements = 718704 4030160 AFLR3 GG : Nodes, Elements = 718834 4030550 AFLR3 GG : Nodes, Elements = 718834 4031082 AFLR3 GG : Nodes, Elements = 718834 4030929 AFLR3 GG : Nodes, Elements = 718902 4031133 AFLR3 GG : Nodes, Elements = 718902 4031395 AFLR3 GG : Nodes, Elements = 718902 4031313 AFLR3 GG : Nodes, Elements = 718948 4031451 AFLR3 GG : Nodes, Elements = 718948 4031642 AFLR3 GG : Nodes, Elements = 718948 4031580 AFLR3 GG : Nodes, Elements = 718969 4031643 AFLR3 GG : Nodes, Elements = 718969 4031735 AFLR3 GG : Nodes, Elements = 718969 4031696 AFLR3 GG : Nodes, Elements = 718984 4031741 AFLR3 GG : Nodes, Elements = 718984 4031806 AFLR3 GG : Nodes, Elements = 718984 4031777 AFLR3 GG : Nodes, Elements = 718993 4031804 AFLR3 GG : Nodes, Elements = 718993 4031837 AFLR3 GG : Nodes, Elements = 718993 4031826 AFLR3 GG : Nodes, Elements = 718998 4031841 AFLR3 GG : Nodes, Elements = 718998 4031865 AFLR3 GG : Nodes, Elements = 718998 4031858 AFLR3 GG : Nodes, Elements = 718999 4031861 AFLR3 GG : Nodes, Elements = 718999 4031864 AFLR3 GG : Nodes, Elements = 718999 4031863 AFLR3 GG : Nodes, Elements = 719001 4031869 AFLR3 GG : Nodes, Elements = 719001 4031880 AFLR3 GG : Nodes, Elements = 719001 4031877 AFLR3 GG : Nodes, Elements = 719182 4032420 AFLR3 GG : Nodes, Elements = 719182 4033198 AFLR3 GG : Nodes, Elements = 719182 4032854 AFLR3 GG : Nodes, Elements = 719277 4033139 AFLR3 GG : Nodes, Elements = 719277 4033530 AFLR3 GG : Nodes, Elements = 719277 4033396 AFLR3 GG : Nodes, Elements = 719330 4033555 AFLR3 GG : Nodes, Elements = 719330 4033763 AFLR3 GG : Nodes, Elements = 719330 4033690 AFLR3 GG : Nodes, Elements = 719355 4033765 AFLR3 GG : Nodes, Elements = 719355 4033857 AFLR3 GG : Nodes, Elements = 719355 4033821 AFLR3 GG : Nodes, Elements = 719369 4033863 AFLR3 GG : Nodes, Elements = 719369 4033917 AFLR3 GG : Nodes, Elements = 719369 4033898 AFLR3 GG : Nodes, Elements = 719383 4033940 AFLR3 GG : Nodes, Elements = 719383 4033992 AFLR3 GG : Nodes, Elements = 719383 4033979 AFLR3 GG : Nodes, Elements = 719395 4034015 AFLR3 GG : Nodes, Elements = 719395 4034054 AFLR3 GG : Nodes, Elements = 719395 4034046 AFLR3 GG : Nodes, Elements = 719407 4034082 AFLR3 GG : Nodes, Elements = 719407 4034126 AFLR3 GG : Nodes, Elements = 719407 4034113 AFLR3 GG : Nodes, Elements = 719420 4034152 AFLR3 GG : Nodes, Elements = 719420 4034200 AFLR3 GG : Nodes, Elements = 719420 4034189 AFLR3 GG : Nodes, Elements = 719433 4034228 AFLR3 GG : Nodes, Elements = 719433 4034279 AFLR3 GG : Nodes, Elements = 719433 4034259 AFLR3 GG : Nodes, Elements = 719444 4034292 AFLR3 GG : Nodes, Elements = 719444 4034335 AFLR3 GG : Nodes, Elements = 719444 4034325 AFLR3 GG : Nodes, Elements = 719456 4034361 AFLR3 GG : Nodes, Elements = 719456 4034413 AFLR3 GG : Nodes, Elements = 719456 4034391 AFLR3 GG : Nodes, Elements = 719466 4034421 AFLR3 GG : Nodes, Elements = 719466 4034464 AFLR3 GG : Nodes, Elements = 719466 4034450 AFLR3 GG : Nodes, Elements = 719473 4034471 AFLR3 GG : Nodes, Elements = 719473 4034501 AFLR3 GG : Nodes, Elements = 719473 4034489 AFLR3 GG : Nodes, Elements = 719480 4034510 AFLR3 GG : Nodes, Elements = 719480 4034538 AFLR3 GG : Nodes, Elements = 719480 4034527 AFLR3 GG : Nodes, Elements = 719485 4034542 AFLR3 GG : Nodes, Elements = 719485 4034561 AFLR3 GG : Nodes, Elements = 719485 4034557 AFLR3 GG : Nodes, Elements = 719487 4034563 AFLR3 GG : Nodes, Elements = 719487 4034569 AFLR3 GG : Nodes, Elements = 719487 4034565 AFLR3 : CPU Time = 3.566 minutes AFLR3 QI : QUALITY IMPROVEMENT AFLR3 QI : Nodes, Elements = 719487 4034565 AFLR3 QI : Nodes, Elements = 713385 4000426 AFLR3 QI : Nodes, Elements = 711508 3989918 AFLR3 QI : Nodes, Elements = 710920 3986583 AFLR3 QI : Nodes, Elements = 710776 3985748 AFLR3 QI : Nodes, Elements = 710748 3985588 AFLR3 QI : Nodes, Elements = 710743 3985561 AFLR3 QI : Nodes, Elements = 710743 4003656 AFLR3 QI : Nodes, Elements = 710743 3982935 AFLR3 QI : Nodes, Elements = 710743 3974745 AFLR3 QI : Nodes, Elements = 710743 3989028 AFLR3 QI : Nodes, Elements = 710743 3974612 AFLR3 QI : Nodes, Elements = 710743 3974054 AFLR3 QI : Nodes, Elements = 710743 3987417 AFLR3 QI : Nodes, Elements = 710743 3974401 AFLR3 QI : Nodes, Elements = 710743 3974017 AFLR3 QI : Nodes, Elements = 710743 3979294 AFLR3 QI : Nodes, Elements = 710743 3973431 AFLR3 QI : Nodes, Elements = 710743 3973015 AFLR3 QI : Nodes, Elements = 710743 3976140 AFLR3 QI : Nodes, Elements = 710743 3972740 AFLR3 QI : Nodes, Elements = 710743 3972458 AFLR3 QI : Nodes, Elements = 710745 3972468 AFLR3 QI : Nodes, Elements = 710745 3975502 AFLR3 QI : Nodes, Elements = 710745 3972483 AFLR3 QI : Nodes, Elements = 710745 3972442 AFLR3 QI : Nodes, Elements = 710745 3974767 AFLR3 QI : Nodes, Elements = 710745 3972343 AFLR3 QI : Nodes, Elements = 710745 3972116 AFLR3 QI : Nodes, Elements = 710745 3972468 AFLR3 : CPU Time = 59.981 seconds AFLR3 QRG: QUALITY GRID RE-GENERATION AFLR3 QRG: Nodes, Elements = 710745 3972468 AFLR3 QRG: Nodes, Elements = 710738 3972415 AFLR3 QRG: Nodes, Elements = 710737 3972412 AFLR3 QRG: Nodes, Elements = 710736 3972407 AFLR3 QRG: Nodes, Elements = 710735 3972404 AFLR3 : CPU Time = 1.637 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 3972404 UG3 : Min, Max Ang = 5.965 164.8 UG3 : Average Angle = 70.2 UG3 : No. Angle>160.0 = 15 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 3972404 UG3 : Min Vol = 2.05e-06 UG3 : Average Vol = 1.5e+04 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol160.0 = 15 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 3972404 UG3 : Min Vol = 2.05e-06 UG3 : Average Vol = 1.5e+04 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.5. Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 4240 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 195.346 m. Reference origin for moment evaluation is (55.4263, 0, 0). Surface(s) where the force coefficients are evaluated: BC_1. Surface(s) plotted in the output file: BC_1. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-8. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_inviscidWing.dat. Surface file name: surface_flow_inviscidWing. Volume file name: flow_inviscidWing. Restart file name: restart_flow_inviscidWing.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | Far-field| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 710735 grid points. 3972404 volume elements. 2 surface markers. 151672 boundary elements in index 0 (Marker = BC_1). 36 boundary elements in index 1 (Marker = BC_2). 3972404 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 5.96352e+10. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 122.726. Mean K: 4.02923. Standard deviation K: 11.9588. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 41.2956| 87.7171| | CV Face Area Aspect Ratio| 1.01507| 3558.28| | CV Sub-Volume Ratio| 1.00331| 26134.6| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 710735| 1/1.00| 10| | 1| 116837| 1/6.08| 8.21704| | 2| 17954| 1/6.51| 6.60187| +-------------------------------------------+ Finding max control volume width. Semi-span length = 97.6729 m. Wetted area = 8795.17 m^2. Area projection in the x-plane = 681.447 m^2, y-plane = 449.382 m^2, z-plane = 4224.13 m^2. Max. coordinate in the x-direction = 123.552 m, y-direction = 97.6729 m, z-direction = 4.71806 m. Min. coordinate in the x-direction = 49.9621 m, y-direction = -97.6729 m, z-direction = -8.47903 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 221265| 1| m^2/s^2| 221265| | Velocity-X| 170.123| 1| m/s| 170.123| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 2.9695| 1| m/s| 2.9695| | Velocity Magnitude| 170.149| 1| m/s| 170.149| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.7822e+01| 0.412038| 2.691946| 2.165035| 5.894884| -0.418144| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.4169e+01| 3.113112| 5.540727| 5.357351| 8.581389| -0.195270| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.1964e+01| 4.878789| 7.415716| 7.123386| 10.367147| 33.442093| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.0492e+01| 6.719770| 9.117839| 9.138945| 12.141986| 82.633563| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.9978e+01| 6.428549| 8.846011| 8.684212| 11.812950| 2.047813| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 2.9323e+01| 6.529556| 9.108075| 9.053230| 11.985107| -187.204252| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 2.8918e+01| 6.551368| 9.076621| 8.775585| 11.970950| 8.293945| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 2.8792e+01| 10.333504| 13.145661| 12.761047| 16.115295| 2.521525| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 2.8604e+01| 10.333474| 13.145657| 12.761157| 16.115295| -177.944708| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 2.8353e+01| 8.917656| 11.735777| 11.457880| 14.726305| -89.948696| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 8.91766| < -8| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_inviscidWing.dat | Writing the forces breakdown file (forces_breakdown_inviscidWing.dat). |CSV file |surface_flow_inviscidWing.csv | Writing the forces breakdown file (forces_breakdown_inviscidWing.dat). |Paraview |flow_inviscidWing.vtu | Writing the forces breakdown file (forces_breakdown_inviscidWing.dat). |Paraview surface |surface_flow_inviscidWing.vtu | Writing the forces breakdown file (forces_breakdown_inviscidWing.dat). +-----------------------------------------------------------------------+ Warning: there are 1401 non-physical points in the solution. Warning: 492 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ ==> Total Forces and Moments --> Cl = 56.960356 Cd = -0.633254 --> Cmx = -1.702452 Cmy = -10.524391 Cmz = 0.029811 --> Cx = -1.627253 Cy = 0.798211 Cz = 56.940628 real 13m38.480s user 13m3.281s sys 0m22.281s + status=0 + set +x ================================================= data/session08/2_su2_InviscidWing.py passed (as expected) ================================================= ================================================= 1_astros_ModalCantilever.py test; + python 1_astros_ModalCantilever.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Running mASTROS pre-analysis... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 425 Number of elements = 482 Number of triangle elements = 0 Number of quadrilateral elements = 482 ---------------------------- Total number of nodes = 425 Total number of elements = 482 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 425 Number of elements = 482 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 482 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Writing analysis cards Writing constraint cards--all constraints for each subcase Writing material cards Writing property cards Writing coordinate system cards ==> Running mASTROS... ==> Running mASTROS post-analysis... Reading Astros OUT file - extracting Eigen-Values! Number of Eigen-Values = 10 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Loading Eigen-Value = 3 Loading Eigen-Value = 4 Loading Eigen-Value = 5 Loading Eigen-Value = 6 Loading Eigen-Value = 7 Loading Eigen-Value = 8 Loading Eigen-Value = 9 Loading Eigen-Value = 10 --> Eigen-frequencies: 1 : 0.00145606 2 : 0.0014575 3 : 0.00332859 4 : 0.00333096 5 : 0.00445176 6 : 0.00445507 7 : 0.00894917 8 : 0.0089521 9 : 0.0110353 10: 0.0110413 real 1m35.086s user 1m17.963s sys 0m30.506s + status=0 + set +x ================================================= data/session09/1_astros_ModalCantilever.py passed (as expected) ================================================= ================================================= 2_astros_ModalSupport.py test; + python 2_astros_ModalSupport.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Running mASTROS pre-analysis... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Name = ribSupport, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 831 Number of elements = 962 Number of triangle elements = 0 Number of quadrilateral elements = 962 Body 2 (of 2) Number of nodes = 1 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 832 Total number of elements = 962 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = ribRootPoint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 2 Name = leftPointLoad, index = 1 Name = ritePointLoad, index = 2 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = ribRoot, index = 1 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Name = ribSupport, index = 6 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 831 Number of elements = 962 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 962 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 832 Combined Number of elements = 963 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 962 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 6 Property name - leftWingSkin Property name - ribSupport Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - ribRootPoint No "constraintType" specified for Constraint tuple ribRootPoint, defaulting to "ZeroDisplacement" No "groupName" specified for Constraint tuple ribRootPoint, going to use constraint name Done getting FEA constraints Getting FEA supports....... Number of supports - 1 Support name - ribRootPoint No "groupName" specified for Support tuple ribRootPoint, going to use support name Done getting FEA supports Getting FEA connections....... Number of connection tuples - 1 Connection name - ribRoot No "groupName" specified for Connection tuple ribRoot! Looking for automatic connections from the use of capsConnectLink for ribRoot 9 automatic connections were made for capsConnect ribRoot (node id 832) Done getting FEA connections Load tuple is NULL - No loads applied Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing connection cards - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Writing analysis cards Writing constraint cards--all constraints for each subcase Writing support cards Writing material cards Writing property cards Writing coordinate system cards ==> Running mASTROS... ==> Running mASTROS post-analysis... Reading Astros OUT file - extracting Eigen-Values! Number of Eigen-Values = 10 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Loading Eigen-Value = 3 Loading Eigen-Value = 4 Loading Eigen-Value = 5 Loading Eigen-Value = 6 Loading Eigen-Value = 7 Loading Eigen-Value = 8 Loading Eigen-Value = 9 Loading Eigen-Value = 10 --> Eigen-frequencies: 1 : 2.14626e-08 2 : 0.00142073 3 : 0.00174522 4 : 0.00323727 5 : 0.00324323 6 : 0.00433058 7 : 0.00512596 8 : 0.00873541 9 : 0.010065 10: 0.010703 real 5m35.391s user 4m24.241s sys 1m31.400s + status=0 + set +x ================================================= data/session09/2_astros_ModalSupport.py passed (as expected) ================================================= ================================================= 3_astros_StaticCantilever.py test; + python 3_astros_StaticCantilever.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Running mASTROS pre-analysis... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 425 Number of elements = 482 Number of triangle elements = 0 Number of quadrilateral elements = 482 ---------------------------- Total number of nodes = 425 Total number of elements = 482 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 425 Number of elements = 482 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 482 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - leftPointLoad No "groupName" specified for Load tuple leftPointLoad, going to use load name Load name - ritePointLoad No "groupName" specified for Load tuple ritePointLoad, going to use load name Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Writing coordinate system cards ==> Running mASTROS... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running mASTROS post-analysis... --> Maximum displacements: --> Tmax 238433.3403112283 --> T1max 16861.9 --> T2max 16414.9 --> T3max 237286.0 real 0m37.437s user 0m42.285s sys 0m8.236s + status=0 + set +x ================================================= data/session09/3_astros_StaticCantilever.py passed (as expected) ================================================= ================================================= 4_astros_Composite.py test; + python 4_astros_Composite.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle ==> Running mASTROS pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 425 Number of elements = 482 Number of triangle elements = 0 Number of quadrilateral elements = 482 ---------------------------- Total number of nodes = 425 Total number of elements = 482 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 425 Number of elements = 482 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 482 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Aluminum No "materialType" specified for Material tuple Aluminum, defaulting to "Isotropic" Material name - Graphite_epoxy Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - leftPointLoad No "groupName" specified for Load tuple leftPointLoad, going to use load name Load name - ritePointLoad No "groupName" specified for Load tuple ritePointLoad, going to use load name Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Writing coordinate system cards ==> Running mASTROS... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running mASTROS post-analysis... --> Maximum displacements: --> Tmax 52594.60117638786 --> T1max 4359.68 --> T2max 3216.5 --> T3max 52322.2 real 0m34.758s user 0m41.116s sys 0m7.756s + status=0 + set +x ================================================= data/session09/4_astros_Composite.py passed (as expected) ================================================= [macys-VM:53141] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/3663265792/sm_segment.macys-VM.502.da590000.0 could be created. ================================================= 6_tacs_StaticCantilever.py test; + python 6_tacs_StaticCantilever.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log [macys-VM:53150] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/4015390720/sm_segment.macys-VM.502.ef560000.0 could be created. ==> Loading geometry from file "../ESP/transport.csm"... ==> Running TACS pre-analysis... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 425 Number of elements = 482 Number of triangle elements = 0 Number of quadrilateral elements = 482 ---------------------------- Total number of nodes = 425 Total number of elements = 482 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 425 Number of elements = 482 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 482 Getting FEA materials....... Number of materials - 1 Material name - aluminum Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - leftWingSkin No "groupName" specified for Load tuple leftWingSkin, going to use load name Load name - riteWingSkin No "groupName" specified for Load tuple riteWingSkin, going to use load name Done getting FEA loads Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing TACS instruction file.... Writing analysis cards Writing load ADD cards Writing constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Writing coordinate system cards [0] Creating TACSAssembler with numOwnedNodes = 425 numElements = 482 [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 2.84, nnz(ILU) = 11729 ==> Running TACS... ==> Running TACS post-analysis... Tacs Analysis Outputs... functional mass = 511406.709389084 functional ks_vmfailure = 0.019135051727266705 real 0m35.007s user 0m40.707s sys 0m7.794s + status=0 + set +x ================================================= data/session09/6_tacs_StaticCantilever.py passed (as expected) ================================================= ================================================= 7_tacs_sizing.py test; + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log + python 7_tacs_sizing.py [macys-VM:53178] shmem: mmap: an error occurred while determining whether or not /var/folders/qk/9zkf0syn149fvhw9mh7hgd5w0000gp/T//ompi.macys-VM.502/jf.0/293797888/sm_segment.macys-VM.502.11830000.0 could be created. ==> Loading geometry from file "../ESP/transport.csm"... ==> Starting optimization... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 3852 Number of elements = 4061 Number of triangle elements = 0 Number of quadrilateral elements = 4061 ---------------------------- Total number of nodes = 3852 Total number of elements = 4061 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 3852 Number of elements = 4061 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 4061 Getting FEA materials....... Number of materials - 1 Material name - aluminum Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - leftWingSkin No "groupName" specified for Load tuple leftWingSkin, going to use load name Load name - riteWingSkin No "groupName" specified for Load tuple riteWingSkin, going to use load name Done getting FEA loads Getting FEA design variables....... Number of design variables - 3 Design_Variable name - ribThk Design_Variable name - skinThk Design_Variable name - sparThk Design_Variable_Relation name - relLeftSkin Design_Variable_Relation name - relRib Design_Variable_Relation name - relRiteSkin Design_Variable_Relation name - relSpar Number of design variable relations - 4 Done getting FEA design variables Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing TACS instruction file.... Writing analysis cards Writing load ADD cards Writing constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Writing coordinate system cards Writing design variable cards Writing design variable relation cards [0] Creating TACSAssembler with numOwnedNodes = 3852 numElements = 4061 [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/data/session09/7_tacs_sizing.py:144: DeprecationWarning: Conversion of an array with ndim > 0 to a scalar is deprecated, and will error in future. Ensure you extract a single element from your array before performing this operation. (Deprecated NumPy 1.25.) xarray[ithick] = float(inputs[thick_dv]) --> ribThk [0.05] --> skinThk [0.003] --> sparThk [0.1] --> mass [351348.85843741] --> ks_vmfailure [0.18465374] --> mass [351348.85843741] --> ks_vmfailure [0.18465374] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00701607]] --> ks_vmfailure skinThk [[-0.7773577]] --> ks_vmfailure sparThk [[-0.00419852]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.001] --> skinThk [0.00739074] --> sparThk [0.001] --> mass [164778.0669354] --> ks_vmfailure [0.18458271] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.2719378]] --> ks_vmfailure skinThk [[-0.30939955]] --> ks_vmfailure sparThk [[-0.20978603]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.001] --> skinThk [0.001] --> sparThk [0.02273644] --> mass [129232.41480384] --> ks_vmfailure [0.20239501] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.001] --> skinThk [0.00647627] --> sparThk [0.00411034] --> mass [159691.72861108] --> ks_vmfailure [0.18468723] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.28428468]] --> ks_vmfailure skinThk [[-0.36623705]] --> ks_vmfailure sparThk [[-0.04561164]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.01797054] --> skinThk [0.001] --> sparThk [0.0012247] --> mass [135761.31328029] --> ks_vmfailure [0.20097432] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00336292] --> skinThk [0.00571377] --> sparThk [0.00370855] --> mass [156359.73946962] --> ks_vmfailure [0.18476613] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.04724024]] --> ks_vmfailure skinThk [[-0.42968566]] --> ks_vmfailure sparThk [[-0.05558717]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00375419] --> skinThk [0.0118629] --> sparThk [0.00560564] --> mass [221348.46863653] --> ks_vmfailure [0.18335024] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00340205] --> skinThk [0.00632869] --> sparThk [0.00389826] --> mass [162858.61238631] --> ks_vmfailure [0.18451389] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.0033671] --> skinThk [0.00577947] --> sparThk [0.00372882] --> mass [157054.09480563] --> ks_vmfailure [0.18473688] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.04660765]] --> ks_vmfailure skinThk [[-0.4208561]] --> ks_vmfailure sparThk [[-0.05458696]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.001] --> skinThk [0.0114244] --> sparThk [0.01236646] --> mass [220187.17353899] --> ks_vmfailure [0.18349008] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.22376311]] --> ks_vmfailure skinThk [[-0.11542908]] --> ks_vmfailure sparThk [[-0.00924892]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00726772] --> skinThk [0.01192034] --> sparThk [0.01564752] --> mass [242329.88959071] --> ks_vmfailure [0.18318718] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00374643] --> skinThk [0.01164171] --> sparThk [0.01380417] --> mass [229889.80331156] --> ks_vmfailure [0.18327675] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.0024241] --> skinThk [0.01153708] --> sparThk [0.01311196] --> mass [225218.27426134] --> ks_vmfailure [0.18333401] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.04342338]] --> ks_vmfailure skinThk [[-0.10932276]] --> ks_vmfailure sparThk [[-0.00862543]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00273423] --> skinThk [0.02300858] --> sparThk [0.02081621] --> mass [351071.64511817] --> ks_vmfailure [0.18265072] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00246133] --> skinThk [0.01291395] --> sparThk [0.01403666] --> mass [240323.8805217] --> ks_vmfailure [0.18319035] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.04030186]] --> ks_vmfailure skinThk [[-0.08766021]] --> ks_vmfailure sparThk [[-0.00725047]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00615236] --> skinThk [0.02577931] --> sparThk [0.00214913] --> mass [361343.3111648] --> ks_vmfailure [0.18263733] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00640621]] --> ks_vmfailure skinThk [[-0.02501964]] --> ks_vmfailure sparThk [[-0.04131406]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00713229] --> skinThk [0.02677304] --> sparThk [0.01682192] --> mass [392609.26145734] --> ks_vmfailure [0.18251681] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00663018] --> skinThk [0.02626385] --> sparThk [0.00930356] --> mass [376588.5352551] --> ks_vmfailure [0.18255199] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00641281] --> skinThk [0.02604342] --> sparThk [0.00604884] --> mass [369653.12752473] --> ks_vmfailure [0.18257185] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00605011]] --> ks_vmfailure skinThk [[-0.02434576]] --> ks_vmfailure sparThk [[-0.00555075]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00973724] --> skinThk [0.04835413] --> sparThk [0.00759182] --> mass [602336.95393367] --> ks_vmfailure [0.18225672] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00752073] --> skinThk [0.03347884] --> sparThk [0.00656306] --> mass [447198.89241696] --> ks_vmfailure [0.18242234] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00423675]] --> ks_vmfailure skinThk [[-0.01486495]] --> ks_vmfailure sparThk [[-0.00451758]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.0124042] --> skinThk [0.0584906] --> sparThk [0.01317179] --> mass [716837.81941702] --> ks_vmfailure [0.18217977] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00154607]] --> ks_vmfailure skinThk [[-0.00498161]] --> ks_vmfailure sparThk [[-0.00115578]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.01929412] --> skinThk [0.0907852] --> sparThk [0.02029644] --> mass [1064336.64937422] --> ks_vmfailure [0.18206339] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00064649]] --> ks_vmfailure skinThk [[-0.00208487]] --> ks_vmfailure sparThk [[-0.00048512]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.02545589] --> skinThk [0.11766677] --> sparThk [0.02722878] --> mass [1355781.80313859] --> ks_vmfailure [0.18201458] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.0003768]] --> ks_vmfailure skinThk [[-0.00124124]] --> ks_vmfailure sparThk [[-0.00027327]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.02816254] --> skinThk [0.12784859] --> sparThk [0.03061479] --> mass [1467935.22745818] --> ks_vmfailure [0.1820012] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00031099]] --> ks_vmfailure skinThk [[-0.00105064]] --> ks_vmfailure sparThk [[-0.00021914]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.02874646] --> skinThk [0.12860075] --> sparThk [0.03166037] --> mass [1478053.31814195] --> ks_vmfailure [0.18200001] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00030043]] --> ks_vmfailure skinThk [[-0.00103744]] --> ks_vmfailure sparThk [[-0.00020726]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.02995586] --> skinThk [0.12773281] --> sparThk [0.03432126] --> mass [1475323.34496521] --> ks_vmfailure [0.18200005] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00028252]] --> ks_vmfailure skinThk [[-0.00104812]] --> ks_vmfailure sparThk [[-0.00018401]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03300208] --> skinThk [0.12582911] --> sparThk [0.04074914] --> mass [1470920.51864181] --> ks_vmfailure [0.18200021] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00024502]] --> ks_vmfailure skinThk [[-0.00107038]] --> ks_vmfailure sparThk [[-0.00014848]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03417055] --> skinThk [0.12543858] --> sparThk [0.04303483] --> mass [1472403.16573053] --> ks_vmfailure [0.18200002] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00023279]] --> ks_vmfailure skinThk [[-0.00107335]] --> ks_vmfailure sparThk [[-0.00014019]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03466542] --> skinThk [0.12523006] --> sparThk [0.04393549] --> mass [1472509.96085976] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022797]] --> ks_vmfailure skinThk [[-0.00107536]] --> ks_vmfailure sparThk [[-0.00013746]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03477347] --> skinThk [0.12519387] --> sparThk [0.0440588] --> mass [1472530.51058047] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022693]] --> ks_vmfailure skinThk [[-0.00107573]] --> ks_vmfailure sparThk [[-0.00013712]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03499382] --> skinThk [0.12513458] --> sparThk [0.04415985] --> mass [1472520.45921217] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022479]] --> ks_vmfailure skinThk [[-0.00107642]] --> ks_vmfailure sparThk [[-0.00013689]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03528599] --> skinThk [0.12508834] --> sparThk [0.04404565] --> mass [1472505.6089541] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022196]] --> ks_vmfailure skinThk [[-0.00107708]] --> ks_vmfailure sparThk [[-0.00013735]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03554749] --> skinThk [0.12509498] --> sparThk [0.04357431] --> mass [1472488.97649504] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.0002194]] --> ks_vmfailure skinThk [[-0.0010773]] --> ks_vmfailure sparThk [[-0.00013892]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03557543] --> skinThk [0.12515335] --> sparThk [0.04308255] --> mass [1472485.55740288] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00021902]] --> ks_vmfailure skinThk [[-0.00107687]] --> ks_vmfailure sparThk [[-0.00014054]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03549811] --> skinThk [0.12518986] --> sparThk [0.04292621] --> mass [1472487.79718265] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.0002197]] --> ks_vmfailure skinThk [[-0.00107651]] --> ks_vmfailure sparThk [[-0.00014103]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03546495] --> skinThk [0.12519741] --> sparThk [0.04292079] --> mass [1472488.35761213] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022001]] --> ks_vmfailure skinThk [[-0.00107642]] --> ks_vmfailure sparThk [[-0.00014104]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03546229] --> skinThk [0.12519748] --> sparThk [0.04292444] --> mass [1472488.40726924] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022004]] --> ks_vmfailure skinThk [[-0.00107641]] --> ks_vmfailure sparThk [[-0.00014103]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03546228] --> skinThk [0.12519745] --> sparThk [0.0429247] --> mass [1472488.40797224] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812601]] --> mass skinThk [[10032748.65480208]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022004]] --> ks_vmfailure skinThk [[-0.00107641]] --> ks_vmfailure sparThk [[-0.00014103]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03546228] --> skinThk [0.12519745] --> sparThk [0.0429247] --> mass [1472488.40757359] --> ks_vmfailure [0.182] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03546228] --> skinThk [0.12519745] --> sparThk [0.0429247] --> mass [1472488.40784458] --> ks_vmfailure [0.182] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03546228] --> skinThk [0.12519745] --> sparThk [0.0429247] --> mass [1472488.40795767] --> ks_vmfailure [0.182] Optimization terminated successfully (Exit mode 0) Current function value: 4.2071097370219075 Iterations: 29 Function evaluations: 42 Gradient evaluations: 29 Optimization Complete ----------------------------------- ==> Optimized value: --> ribThk [0.03546228] --> skinThk [0.12519745] --> sparThk [0.0429247] real 2m20.696s user 2m26.881s sys 0m9.217s + status=0 + set +x ================================================= data/session09/7_tacs_sizing.py passed (as expected) ================================================= ================================================= 2_aeroelastic_Iterative_SU2_Astros.py test; + python 2_aeroelastic_Iterative_SU2_Astros.py + tee -a /Users/jenkins/workspace/ESP_bPreBuilt/CAPS/training/2023/training.log MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle ==> Running SU2 pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - leftWing Mesh sizing name - riteWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0.5 1 2 3 6 EGADS : 2 Yes 0 0 1 0.5 1 1 4 5 EGADS : 3 Yes 0 0 1 0.5 1 1 4 8 EGADS : 4 Yes 0 0 1 0.5 1 2 3 5 EGADS : 5 Yes 0 0 1 0.5 1 2 4 EGADS : 6 Yes 0 0 1 0.5 1 1 7 8 EGADS : 7 Yes 0 0 1 0.5 1 6 9 10 EGADS : 8 Yes 0 0 1 0.5 1 3 6 9 EGADS : 9 Yes 0 0 1 0.5 1 7 8 10 EGADS : 10 Yes 0 0 1 0.5 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 11135.8 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 16 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 242 426 0 AFLR4 : Nodes, Trias,Quads= 203 348 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 301 529 0 AFLR4 : Nodes, Trias,Quads= 178 283 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 233 409 0 AFLR4 : Nodes, Trias,Quads= 189 321 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 292 511 0 AFLR4 : Nodes, Trias,Quads= 174 275 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 9 10 0 AFLR4 : Nodes, Trias,Quads= 6 4 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 241 424 0 AFLR4 : Nodes, Trias,Quads= 202 346 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 302 531 0 AFLR4 : Nodes, Trias,Quads= 177 281 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 235 413 0 AFLR4 : Nodes, Trias,Quads= 189 321 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 293 513 0 AFLR4 : Nodes, Trias,Quads= 173 273 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 9 10 0 AFLR4 : Nodes, Trias,Quads= 6 4 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 1238 2468 542 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 1238 2468 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1695 3170 0 AFLR4 : Nodes, Trias,Quads= 1371 2522 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 3139 5972 0 AFLR4 : Nodes, Trias,Quads= 1805 3304 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 1597 2983 0 AFLR4 : Nodes, Trias,Quads= 1311 2411 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 3114 5923 0 AFLR4 : Nodes, Trias,Quads= 1786 3267 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 36 46 0 AFLR4 : Nodes, Trias,Quads= 24 22 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1691 3162 0 AFLR4 : Nodes, Trias,Quads= 1376 2532 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 3162 6018 0 AFLR4 : Nodes, Trias,Quads= 1802 3298 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 1600 2989 0 AFLR4 : Nodes, Trias,Quads= 1326 2441 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 3109 5913 0 AFLR4 : Nodes, Trias,Quads= 1784 3263 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 36 46 0 AFLR4 : Nodes, Trias,Quads= 24 22 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 12 14 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 11563 23118 2164 OVERALL : CPU Time = 0.363 seconds Body 1 (of 2) Number of nodes = 11543 Number of elements = 23082 Number of triangle elements = 23082 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 20 Number of elements = 36 Number of triangle elements = 36 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11563 Total number of elements = 23118 Total number of triangle elements = 23118 Total number of quadrilateral elements = 0 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Getting volume mesh UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.18.1 AFLR2 : Version Date 06/11/24 @ 05:52PM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 06/11/24 @ 06:29PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.15 AFLR4 : Version Date 07/19/24 @ 07:04PM AFLR4 : Compile OS Darwin 23.5.0 x86_64 AFLR4 : Compile Date 07/19/24 @ 07:21PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.1 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0.5 1 2 3 6 EGADS : 2 Yes 0 0 1 0.5 1 1 4 5 EGADS : 3 Yes 0 0 1 0.5 1 1 4 8 EGADS : 4 Yes 0 0 1 0.5 1 2 3 5 EGADS : 5 Yes 0 0 1 0.5 1 2 4 EGADS : 6 Yes 0 0 1 0.5 1 1 7 8 EGADS : 7 Yes 0 0 1 0.5 1 6 9 10 EGADS : 8 Yes 0 0 1 0.5 1 3 6 9 EGADS : 9 Yes 0 0 1 0.5 1 7 8 10 EGADS : 10 Yes 0 0 1 0.5 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 13.1976 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 428.309 AFLR4 : Abs Min Surf Spacing = 0.032994 AFLR4 : Min Surf Spacing = 0.065988 AFLR4 : Max Surf Spacing = 1.31976 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD AFLR4 : 2 CAD geometry 0 STD AFLR4 : 3 CAD geometry 0 STD AFLR4 : 4 CAD geometry 0 STD AFLR4 : 5 CAD geometry 0 STD AFLR4 : 6 CAD geometry 0 STD AFLR4 : 7 CAD geometry 0 STD AFLR4 : 8 CAD geometry 0 STD AFLR4 : 9 CAD geometry 0 STD AFLR4 : 10 CAD geometry 0 STD AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR43 : INPUT SURFACE MESH FROM TESS AFLR43 : Quad Surface Faces= 0 AFLR43 : Tria Surface Faces= 23118 AFLR43 : Nodes = 11563 UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR3 : --------------------------------------- AFLR3 : AFLR3 LIBRARY AFLR3 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR3 : TETRAHEDRAL GRID GENERATOR AFLR3 : Version Number 16.32.50 AFLR3 : Version Date 10/31/23 @ 06:31PM AFLR3 : Compile OS Darwin 22.6.0 x86_64 AFLR3 : Compile Date 11/01/23 @ 12:19PM AFLR3 : Copyright 1994-2021, D.L. Marcum AFLR3 : --------------------------------------- AFLR3 IC : INPUT SURFACE GRID CHECK AFLR3 IC : Nodes, Elements = 11563 0 UG3 : Boundary Conditions UG3 : B-Face ID Boundary Condition UG3 : 1 Solid UG3 : 2 Solid UG3 : 3 Solid UG3 : 4 Solid UG3 : 5 Solid UG3 : 6 Solid UG3 : 7 Solid UG3 : 8 Solid UG3 : 9 Solid UG3 : 10 Solid UG3 : 11 FarField UG3 : 12 FarField UG3 : 13 FarField UG3 : 14 FarField UG3 : 15 FarField UG3 : 16 FarField AFLR3 : CPU Time = 0.036 seconds AFLR3 IG : INITIAL VOLUME GRID GENERATION AFLR3 IG : Nodes, Elements = 11563 0 AFLR3 IG : Nodes, Elements = 8 10 AFLR3 IG : Nodes, Elements = 2314 16716 AFLR3 IG : Nodes, Elements = 4628 33740 AFLR3 IG : Nodes, Elements = 6942 53623 AFLR3 IG : Nodes, Elements = 9256 74438 AFLR3 IG : Nodes, Elements = 11570 95707 AFLR3 IG : Nodes, Elements = 11570 95483 AFLR3 IG : Nodes, Elements = 11563 61784 AFLR3 IG : Nodes, Elements = 11563 61867 AFLR3 IG : Nodes, Elements = 11563 39409 AFLR3 IG : Nodes, Elements = 11563 34878 AFLR3 : CPU Time = 0.828 seconds AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION AFLR3 GG : Nodes, Elements = 11563 34878 AFLR3 GG : Nodes, Elements = 16496 49957 AFLR3 GG : Nodes, Elements = 16496 70754 AFLR3 GG : Nodes, Elements = 16496 65441 AFLR3 GG : Nodes, Elements = 20474 77967 AFLR3 GG : Nodes, Elements = 20474 92760 AFLR3 GG : Nodes, Elements = 20474 87583 AFLR3 GG : Nodes, Elements = 24849 101329 AFLR3 GG : Nodes, Elements = 24849 118564 AFLR3 GG : Nodes, Elements = 24849 113057 AFLR3 GG : Nodes, Elements = 29511 127335 AFLR3 GG : Nodes, Elements = 29511 145756 AFLR3 GG : Nodes, Elements = 29511 140522 AFLR3 GG : Nodes, Elements = 34372 155355 AFLR3 GG : Nodes, Elements = 34372 174698 AFLR3 GG : Nodes, Elements = 34372 169453 AFLR3 GG : Nodes, Elements = 39230 184208 AFLR3 GG : Nodes, Elements = 39230 203201 AFLR3 GG : Nodes, Elements = 39230 198077 AFLR3 GG : Nodes, Elements = 44067 212787 AFLR3 GG : Nodes, Elements = 44067 231574 AFLR3 GG : Nodes, Elements = 44067 226725 AFLR3 GG : Nodes, Elements = 48793 241074 AFLR3 GG : Nodes, Elements = 48793 259704 AFLR3 GG : Nodes, Elements = 48793 254826 AFLR3 GG : Nodes, Elements = 53425 268867 AFLR3 GG : Nodes, Elements = 53425 286996 AFLR3 GG : Nodes, Elements = 53425 282350 AFLR3 GG : Nodes, Elements = 57940 296060 AFLR3 GG : Nodes, Elements = 57940 313822 AFLR3 GG : Nodes, Elements = 57940 309079 AFLR3 GG : Nodes, Elements = 62354 322460 AFLR3 GG : Nodes, Elements = 62354 339840 AFLR3 GG : Nodes, Elements = 62354 335275 AFLR3 GG : Nodes, Elements = 66713 348501 AFLR3 GG : Nodes, Elements = 66713 365339 AFLR3 GG : Nodes, Elements = 66713 361041 AFLR3 GG : Nodes, Elements = 70982 373968 AFLR3 GG : Nodes, Elements = 70982 390795 AFLR3 GG : Nodes, Elements = 70982 386488 AFLR3 GG : Nodes, Elements = 75066 398863 AFLR3 GG : Nodes, Elements = 75066 414944 AFLR3 GG : Nodes, Elements = 75066 410652 AFLR3 GG : Nodes, Elements = 79089 422849 AFLR3 GG : Nodes, Elements = 79089 438593 AFLR3 GG : Nodes, Elements = 79089 434590 AFLR3 GG : Nodes, Elements = 82990 446388 AFLR3 GG : Nodes, Elements = 82990 461737 AFLR3 GG : Nodes, Elements = 82990 457790 AFLR3 GG : Nodes, Elements = 86679 468952 AFLR3 GG : Nodes, Elements = 86679 483418 AFLR3 GG : Nodes, Elements = 86679 479677 AFLR3 GG : Nodes, Elements = 90286 490569 AFLR3 GG : Nodes, Elements = 90286 504620 AFLR3 GG : Nodes, Elements = 90286 501105 AFLR3 GG : Nodes, Elements = 93781 511664 AFLR3 GG : Nodes, Elements = 93781 525309 AFLR3 GG : Nodes, Elements = 93781 521819 AFLR3 GG : Nodes, Elements = 97084 531790 AFLR3 GG : Nodes, Elements = 97084 544813 AFLR3 GG : Nodes, Elements = 97084 541433 AFLR3 GG : Nodes, Elements = 100278 551068 AFLR3 GG : Nodes, Elements = 100278 563612 AFLR3 GG : Nodes, Elements = 100278 560342 AFLR3 GG : Nodes, Elements = 103376 569686 AFLR3 GG : Nodes, Elements = 103376 581814 AFLR3 GG : Nodes, Elements = 103376 578764 AFLR3 GG : Nodes, Elements = 106363 587778 AFLR3 GG : Nodes, Elements = 106363 599392 AFLR3 GG : Nodes, Elements = 106363 596512 AFLR3 GG : Nodes, Elements = 109168 604963 AFLR3 GG : Nodes, Elements = 109168 615928 AFLR3 GG : Nodes, Elements = 109168 613178 AFLR3 GG : Nodes, Elements = 111839 621232 AFLR3 GG : Nodes, Elements = 111839 631817 AFLR3 GG : Nodes, Elements = 111839 629118 AFLR3 GG : Nodes, Elements = 114346 636681 AFLR3 GG : Nodes, Elements = 114346 646453 AFLR3 GG : Nodes, Elements = 114346 644024 AFLR3 GG : Nodes, Elements = 116718 651184 AFLR3 GG : Nodes, Elements = 116718 660339 AFLR3 GG : Nodes, Elements = 116718 658008 AFLR3 GG : Nodes, Elements = 119006 664904 AFLR3 GG : Nodes, Elements = 119006 674034 AFLR3 GG : Nodes, Elements = 119006 671709 AFLR3 GG : Nodes, Elements = 121097 678015 AFLR3 GG : Nodes, Elements = 121097 686107 AFLR3 GG : Nodes, Elements = 121097 684043 AFLR3 GG : Nodes, Elements = 123032 689878 AFLR3 GG : Nodes, Elements = 123032 697499 AFLR3 GG : Nodes, Elements = 123032 695602 AFLR3 GG : Nodes, Elements = 124821 701006 AFLR3 GG : Nodes, Elements = 124821 707974 AFLR3 GG : Nodes, Elements = 124821 706183 AFLR3 GG : Nodes, Elements = 126503 711252 AFLR3 GG : Nodes, Elements = 126503 717957 AFLR3 GG : Nodes, Elements = 126503 716225 AFLR3 GG : Nodes, Elements = 128091 721014 AFLR3 GG : Nodes, Elements = 128091 727222 AFLR3 GG : Nodes, Elements = 128091 725653 AFLR3 GG : Nodes, Elements = 129503 729914 AFLR3 GG : Nodes, Elements = 129503 735418 AFLR3 GG : Nodes, Elements = 129503 734022 AFLR3 GG : Nodes, Elements = 130827 738013 AFLR3 GG : Nodes, Elements = 130827 743263 AFLR3 GG : Nodes, Elements = 130827 741872 AFLR3 GG : Nodes, Elements = 132013 745441 AFLR3 GG : Nodes, Elements = 132013 750146 AFLR3 GG : Nodes, Elements = 132013 748949 AFLR3 GG : Nodes, Elements = 133097 752213 AFLR3 GG : Nodes, Elements = 133097 756440 AFLR3 GG : Nodes, Elements = 133097 755409 AFLR3 GG : Nodes, Elements = 134096 758410 AFLR3 GG : Nodes, Elements = 134096 762353 AFLR3 GG : Nodes, Elements = 134096 761358 AFLR3 GG : Nodes, Elements = 135016 764123 AFLR3 GG : Nodes, Elements = 135016 767759 AFLR3 GG : Nodes, Elements = 135016 766857 AFLR3 GG : Nodes, Elements = 135836 769326 AFLR3 GG : Nodes, Elements = 135836 772483 AFLR3 GG : Nodes, Elements = 135836 771678 AFLR3 GG : Nodes, Elements = 136555 773841 AFLR3 GG : Nodes, Elements = 136555 776675 AFLR3 GG : Nodes, Elements = 136555 775958 AFLR3 GG : Nodes, Elements = 137193 777874 AFLR3 GG : Nodes, Elements = 137193 780391 AFLR3 GG : Nodes, Elements = 137193 779778 AFLR3 GG : Nodes, Elements = 137745 781434 AFLR3 GG : Nodes, Elements = 137745 783542 AFLR3 GG : Nodes, Elements = 137745 783014 AFLR3 GG : Nodes, Elements = 138168 784283 AFLR3 GG : Nodes, Elements = 138168 786000 AFLR3 GG : Nodes, Elements = 138168 785511 AFLR3 GG : Nodes, Elements = 138509 786534 AFLR3 GG : Nodes, Elements = 138509 787906 AFLR3 GG : Nodes, Elements = 138509 787512 AFLR3 GG : Nodes, Elements = 138768 788291 AFLR3 GG : Nodes, Elements = 138768 789371 AFLR3 GG : Nodes, Elements = 138768 789056 AFLR3 GG : Nodes, Elements = 138948 789596 AFLR3 GG : Nodes, Elements = 138948 790332 AFLR3 GG : Nodes, Elements = 138948 790114 AFLR3 GG : Nodes, Elements = 139074 790493 AFLR3 GG : Nodes, Elements = 139074 791015 AFLR3 GG : Nodes, Elements = 139074 790850 AFLR3 GG : Nodes, Elements = 139160 791108 AFLR3 GG : Nodes, Elements = 139160 791448 AFLR3 GG : Nodes, Elements = 139160 791345 AFLR3 GG : Nodes, Elements = 139211 791498 AFLR3 GG : Nodes, Elements = 139211 791701 AFLR3 GG : Nodes, Elements = 139211 791640 AFLR3 GG : Nodes, Elements = 139242 791733 AFLR3 GG : Nodes, Elements = 139242 791861 AFLR3 GG : Nodes, Elements = 139242 791819 AFLR3 GG : Nodes, Elements = 139249 791840 AFLR3 GG : Nodes, Elements = 139249 791873 AFLR3 GG : Nodes, Elements = 139249 791858 AFLR3 GG : Nodes, Elements = 139252 791867 AFLR3 GG : Nodes, Elements = 139252 791877 AFLR3 GG : Nodes, Elements = 139252 791873 AFLR3 GG : Nodes, Elements = 139253 791876 AFLR3 GG : Nodes, Elements = 139253 791883 AFLR3 GG : Nodes, Elements = 139253 791878 AFLR3 GG : Nodes, Elements = 139260 791899 AFLR3 GG : Nodes, Elements = 139260 791926 AFLR3 GG : Nodes, Elements = 139260 791914 AFLR3 GG : Nodes, Elements = 139262 791920 AFLR3 GG : Nodes, Elements = 139262 791928 AFLR3 GG : Nodes, Elements = 139262 791923 AFLR3 GG : Nodes, Elements = 139263 791926 AFLR3 GG : Nodes, Elements = 139263 791930 AFLR3 GG : Nodes, Elements = 139263 791927 AFLR3 : CPU Time = 16.631 seconds AFLR3 QI : QUALITY IMPROVEMENT AFLR3 QI : Nodes, Elements = 139263 791927 AFLR3 QI : Nodes, Elements = 138470 787420 AFLR3 QI : Nodes, Elements = 138371 786852 AFLR3 QI : Nodes, Elements = 138355 786758 AFLR3 QI : Nodes, Elements = 138353 786746 AFLR3 QI : Nodes, Elements = 138353 790318 AFLR3 QI : Nodes, Elements = 138353 786519 AFLR3 QI : Nodes, Elements = 138353 784972 AFLR3 QI : Nodes, Elements = 138353 785336 AFLR3 QI : Nodes, Elements = 138353 784715 AFLR3 QI : Nodes, Elements = 138353 784549 AFLR3 : CPU Time = 2.805 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 784549 UG3 : Min, Max Ang = 3.352 156.2 UG3 : Average Angle = 70.2 UG3 : No. Angle>160.0 = 0 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 784549 UG3 : Min Vol = 0.00102 UG3 : Average Vol = 7.6e+04 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol160.0 = 0 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 784549 UG3 : Min Vol = 0.00102 UG3 : Average Vol = 7.6e+04 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 4240 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 195.346 m. Reference origin for moment evaluation is (55.4263, 0, 0). Surface(s) where the force coefficients are evaluated: BC_1. Surface(s) plotted in the output file: BC_1. Surface(s) affected by the design variables: BC_1. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat. Surface file name: surface_flow_aeroelasticIterative. Volume file name: flow_aeroelasticIterative. Restart file name: restart_flow_aeroelasticIterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | Far-field| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 138353 grid points. 784549 volume elements. 2 surface markers. 23082 boundary elements in index 0 (Marker = BC_1). 36 boundary elements in index 1 (Marker = BC_2). 784549 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 5.96352e+10. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 29.8369. Mean K: 1.54048. Standard deviation K: 3.02418. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 53.2849| 87.2163| | CV Face Area Aspect Ratio| 1.05837| 624.248| | CV Sub-Volume Ratio| 1.03302| 9859.67| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 138353| 1/1.00| 10| | 1| 22635| 1/6.11| 8.20393| | 2| 3435| 1/6.59| 6.5639| +-------------------------------------------+ Finding max control volume width. Semi-span length = 97.6729 m. Wetted area = 8661.74 m^2. Area projection in the x-plane = 677.811 m^2, y-plane = 441.377 m^2, z-plane = 4150.71 m^2. Max. coordinate in the x-direction = 123.552 m, y-direction = 97.6729 m, z-direction = 4.71806 m. Min. coordinate in the x-direction = 50 m, y-direction = -97.6729 m, z-direction = -8.47948 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 6.3736e+00| 0.748156| 2.907167| 2.644419| 6.217262| -0.776081| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.9463e+00| 2.193422| 4.562457| 4.459169| 7.653331| -0.476445| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.7283e+00| 3.220298| 5.616950| 5.416508| 8.692127| 1.468288| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 5.6391e+00| 4.326237| 6.696479| 6.559465| 9.797905| -16.210089| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 5.5928e+00| 5.449284| 7.811591| 7.705956| 10.920940| -8.274538| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 5.44928| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticIterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |CSV file |surface_flow_aeroelasticIterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |Tecplot binary |flow_aeroelasticIterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |Tecplot binary surface |surface_flow_aeroelasticIterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ ==> Running SU2 post-analysis... ==> Running ASTROS pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 425 Number of elements = 482 Number of triangle elements = 0 Number of quadrilateral elements = 482 ---------------------------- Total number of nodes = 425 Total number of elements = 482 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 425 Number of elements = 482 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 482 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureAero No "groupName" specified for Load tuple pressureAero, going to use load name Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 11543 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure' Rank 0: src = 2.608592e+12, tgt = 2.608592e+12, diff = 1.062328e+03 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 11543 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure' Rank 0: src = 2.590668e+12, tgt = 2.590668e+12, diff = 9.744878e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 11543 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure' Rank 0: src = 8.484994e+08, tgt = 8.485003e+08, diff = 9.237144e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 11543 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure' Rank 0: src = 8.699308e+08, tgt = 8.699317e+08, diff = 8.929823e+02 Extracting external pressure loads from data transfer.... TransferName = upperWing Number of Elements = 98 (total = 98) Extracting external pressure loads from data transfer.... TransferName = lowerWing Number of Elements = 98 (total = 196) Extracting external pressure loads from data transfer.... TransferName = leftTip Number of Elements = 17 (total = 213) Extracting external pressure loads from data transfer.... TransferName = riteTip Number of Elements = 17 (total = 230) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Writing coordinate system cards ==> Running mASTROS...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running ASTROS post-analysis... ==> Running SU2 pre-analysis... Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 1 Done boundary flags Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticIterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" ==> Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | Far-field| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 138353 grid points. 784549 volume elements. 2 surface markers. 23082 boundary elements in index 0 (Marker = BC_1). 36 boundary elements in index 1 (Marker = BC_2). 784549 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 5.96352e+10. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 90.932321 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.1 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2024, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see . | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 4240 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 195.346 m. Reference origin for moment evaluation is (55.4263, 0, 0). Surface(s) where the force coefficients are evaluated: BC_1. Surface(s) plotted in the output file: BC_1. Surface(s) affected by the design variables: BC_1. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat. Surface file name: surface_flow_aeroelasticIterative. Volume file name: flow_aeroelasticIterative. Restart file name: restart_flow_aeroelasticIterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | Far-field| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 138353 grid points. 784549 volume elements. 2 surface markers. 23082 boundary elements in index 0 (Marker = BC_1). 36 boundary elements in index 1 (Marker = BC_2). 784549 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 161258 TETRAHEDRON volume elements. There has been a re-orientation of 6205 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 5.96714e+10. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 50.446. Mean K: 1.91664. Standard deviation K: 2.5278. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 1.20947| 85.7885| | CV Face Area Aspect Ratio| 1.07738| 5213.62| | CV Sub-Volume Ratio| 1.05919| 3.08401e+06| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 138353| 1/1.00| 10| | 1| 22610| 1/6.12| 8.20091| | 2| 3433| 1/6.59| 6.56263| +-------------------------------------------+ Finding max control volume width. Semi-span length = 112.067 m. Wetted area = 687669 m^2. Area projection in the x-plane = 192396 m^2, y-plane = 170768 m^2, z-plane = 62406.8 m^2. Max. coordinate in the x-direction = 176.384 m, y-direction = 112.067 m, z-direction = 225.336 m. Min. coordinate in the x-direction = 43.9729 m, y-direction = -116.9 m, z-direction = -695.222 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 5.5746e+00| 4.679017| 7.655201| 7.476894| 10.148122| -0.028447| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 6.8386e+00| 4.935745| 7.624566| 7.419008| 10.339948| 0.000774| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 7.2443e+00| 5.516931| 7.941695| 7.846123| 10.991518| 0.005062| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 8.1423e+00| 6.288641| 8.672463| 8.604690| 11.749243| 0.020913| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 8.6891e+00| 6.376675| 8.830266| 8.721765| 11.869846| 0.031217| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 6.37668| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticIterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |CSV file |surface_flow_aeroelasticIterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |Tecplot binary |flow_aeroelasticIterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |Tecplot binary surface |surface_flow_aeroelasticIterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). +-----------------------------------------------------------------------+ Warning: there are 9965 non-physical points in the solution. Warning: 3124 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ ==> Running SU2 post-analysis... ==> Running ASTROS pre-analysis... Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 11543 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure' Rank 0: src = 1.582269e+12, tgt = 1.582269e+12, diff = 6.849866e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 11543 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure' Rank 0: src = 1.353977e+12, tgt = 1.353977e+12, diff = 1.758545e+00 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 11543 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure' Rank 0: src = 3.008368e+08, tgt = 3.008449e+08, diff = 8.122931e+03 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 11543 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure' Rank 0: src = 2.657267e+08, tgt = 2.657268e+08, diff = 1.194048e+02 Extracting external pressure loads from data transfer.... TransferName = upperWing Number of Elements = 98 (total = 98) Extracting external pressure loads from data transfer.... TransferName = lowerWing Number of Elements = 98 (total = 196) Extracting external pressure loads from data transfer.... TransferName = leftTip Number of Elements = 17 (total = 213) Extracting external pressure loads from data transfer.... TransferName = riteTip Number of Elements = 17 (total = 230) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Writing coordinate system cards ==> Running mASTROS...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running ASTROS post-analysis... real 5m50.184s user 5m5.247s sys 0m35.629s + status=0 + set +x ================================================= data/session10/2_aeroelastic_Iterative_SU2_Astros.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Did not run examples for: session08 cart3d session08 fun3d session09 nastran session11 fun3d+astros ================================================= All tests pass! ================================================= ================================================= + cd /Users/jenkins/workspace/ESP_bPreBuilt + mkdir -p /Users/jenkins/workspace/ESP_bPreBuilt/test/plugs + cd /Users/jenkins/workspace/ESP_bPreBuilt/test/plugs + find /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs -name 'plugs0*.csm' + sort -f + awk '{ n=split($0, a, ";"); for(i=1; i<=n; i+=2) print a[i] }' /Users/jenkins/workspace/ESP_bPreBuilt/JenkinsESP/data/plugs/plugsFailure.txt + cp /Users/jenkins/workspace/ESP_bPreBuilt/JenkinsESP/data/plugs/plugsIgnore.txt . + set +x Testing CSM files: data/Plugs/plugs0a.csm data/Plugs/plugs0b.csm data/Plugs/plugs0c.csm data/Plugs/plugs0d.csm total 50872 -rw-r--r-- 1 jenkins staff 1.2M Jul 26 12:16 ASTRO.D01 -rw-r--r-- 1 jenkins staff 277K Jul 26 12:16 ASTRO.IDX -rwxr-xr-x 1 jenkins staff 129K Jul 26 12:17 ESPxddm -rwxr-xr-x 1 jenkins staff 210K Jul 26 12:17 Slugs -rwxr-xr-x 1 jenkins staff 85K Jul 26 12:17 TestFit -rwxr-xr-x 1 jenkins staff 1.8M Jul 26 12:16 avl -rwxr-xr-x 1 jenkins staff 34K Jul 26 12:17 cart3dTest -rwxr-xr-x 1 jenkins staff 34K Jul 26 12:17 egads2cart -rwxr-xr-x 1 jenkins staff 70K Jul 26 12:17 egads2cgt -rwxr-xr-x 1 jenkins staff 416K Jul 26 12:17 friction -rwxr-xr-x 1 jenkins staff 8.9M Jul 26 12:16 mastros.exe -rwxr-xr-x 1 jenkins staff 2.2M Jul 26 12:16 mses -rwxr-xr-x 1 jenkins staff 2.5M Jul 26 12:16 mset -rwxr-xr-x 1 jenkins staff 34K Jul 26 12:17 phaseUtil -rw-r--r-- 1 jenkins staff 1.6K Jul 28 00:53 pod.egads -rw-r--r-- 1 jenkins staff 0B Jul 28 00:53 port7681.jrnl -rwxr-xr-x 1 jenkins staff 1.2M Jul 26 12:16 pplot -rwxr-xr-x 1 jenkins staff 1.2M Jul 26 12:16 pxplot -rwxr-xr-x 1 jenkins staff 68K Jul 26 12:17 sensCSM -rwxr-xr-x 1 jenkins staff 206K Jul 26 12:17 serveCSM -rwxr-xr-x 1 jenkins staff 174K Jul 26 12:17 serveESP -rwxr-xr-x 1 jenkins staff 51K Jul 26 12:17 vCurvature -rwxr-xr-x 1 jenkins staff 35K Jul 26 12:17 vGeom -rwxr-xr-x 1 jenkins staff 52K Jul 26 12:17 vTess -rwxr-xr-x 1 jenkins staff 2.0M Jul 26 12:17 vTesstatic -rw-r--r-- 1 jenkins staff 196K Jul 28 00:53 wingMultiModel.bdf -rwxr-xr-x 1 jenkins staff 1.8M Jul 26 12:16 xfoil ( 1 / 4 ) data/Plugs/plugs0a.csm; ++ /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveCSM /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/plugs0a.csm -outLevel 0 -plugs 25 -plot /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/plugs0.cloud -batch -verify -jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/buildFinal.jrnl WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/verify_7.8.1/plugs0a.vfy", so verification is being skipped =================================== PLUGS with 4562 points in the cloud =================================== PLUGS phase1: match bounding boxes PLUGS phase2: match cloud points Starting pass 1 (of 25) of phase2 Pass 1 converged, dmax= 5.416e-07, rmsbest= 6.132e-04, reclass= 4562, unclass= 0 Starting pass 2 (of 25) of phase2 Pass 2 converged, dmax= 5.366e-07, rmsbest= 7.097e-04, reclass= 2, unclass= 0 Starting pass 3 (of 25) of phase2 Phase2 passes converged because points are classified same as previous pass ==> Opening input journal file "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/buildFinal.jrnl" ==> Closing input journal file ==> serveCSM completed successfully with no verification data real 0m19.657s user 0m13.462s sys 0m2.321s ++ set +x data/Plugs/plugs0a passed (as expected) -------------------------------------------------------------------------------------------------- ( 2 / 4 ) data/Plugs/plugs0b.csm; ++ /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveCSM /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/plugs0b.csm -outLevel 0 -plugs 25 -plot /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/plugs0.cloud -batch -verify -jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/buildFinal.jrnl WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/verify_7.8.1/plugs0b.vfy", so verification is being skipped =================================== PLUGS with 4562 points in the cloud =================================== PLUGS phase1: match bounding boxes PLUGS phase2: match cloud points Starting pass 1 (of 25) of phase2 Pass 1 converged, dmax= 3.039e-07, rmsbest= 4.036e-02, reclass= 4562, unclass= 0 Starting pass 2 (of 25) of phase2 Pass 2 converged, dmax= 2.814e-07, rmsbest= 1.924e-03, reclass= 1033, unclass= 0 Starting pass 3 (of 25) of phase2 Pass 3 converged, dmax= 4.494e-07, rmsbest= 5.920e-04, reclass= 473, unclass= 0 Starting pass 4 (of 25) of phase2 Pass 4 converged, dmax= 5.366e-07, rmsbest= 7.097e-04, reclass= 17, unclass= 0 Starting pass 5 (of 25) of phase2 Phase2 passes converged because points are classified same as previous pass ==> Opening input journal file "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/buildFinal.jrnl" ==> Closing input journal file ==> serveCSM completed successfully with no verification data real 0m13.154s user 0m15.398s sys 0m0.334s ++ set +x data/Plugs/plugs0b passed (as expected) -------------------------------------------------------------------------------------------------- ( 3 / 4 ) data/Plugs/plugs0c.csm; ++ /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveCSM /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/plugs0c.csm -outLevel 0 -plugs 25 -plot /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/plugs0.cloud -batch -verify -jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/buildFinal.jrnl WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/verify_7.8.1/plugs0c.vfy", so verification is being skipped =================================== PLUGS with 4562 points in the cloud =================================== PLUGS phase1: match bounding boxes PLUGS phase2: match cloud points Starting pass 1 (of 25) of phase2 Pass 1 ran out of iterations, rmsbest= 1.677e-01, reclass= 4562, unclass= 554 Starting pass 2 (of 25) of phase2 Pass 2 converged, dmax= 4.016e-07, rmsbest= 6.330e-02, reclass= 1676, unclass= 0 Starting pass 3 (of 25) of phase2 Pass 3 converged, dmax= 1.881e-07, rmsbest= 8.736e-03, reclass= 791, unclass= 0 Starting pass 4 (of 25) of phase2 Pass 4 converged, dmax= 3.081e-07, rmsbest= 1.037e-03, reclass= 428, unclass= 0 Starting pass 5 (of 25) of phase2 Pass 5 converged, dmax= 5.816e-07, rmsbest= 7.097e-04, reclass= 109, unclass= 0 Starting pass 6 (of 25) of phase2 Phase2 passes converged because points are classified same as previous pass ==> Opening input journal file "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/buildFinal.jrnl" ==> Closing input journal file ==> serveCSM completed successfully with no verification data real 0m32.024s user 0m46.122s sys 0m0.759s ++ set +x data/Plugs/plugs0c passed (as expected) -------------------------------------------------------------------------------------------------- ( 4 / 4 ) data/Plugs/plugs0d.csm; ++ /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/bin/serveCSM /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/plugs0d.csm -outLevel 0 -plugs 25 -plot /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/plugs0.cloud -batch -verify -jrnl /Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/buildFinal.jrnl WARNING:: cannot open "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/verify_7.8.1/plugs0d.vfy", so verification is being skipped =================================== PLUGS with 4562 points in the cloud =================================== PLUGS phase1: match bounding boxes PLUGS phase2: match cloud points Starting pass 1 (of 25) of phase2 Pass 1 ran out of iterations, rmsbest= 1.677e-01, reclass= 4562, unclass= 554 Starting pass 2 (of 25) of phase2 Pass 2 converged, dmax= 4.016e-07, rmsbest= 6.330e-02, reclass= 1676, unclass= 0 Starting pass 3 (of 25) of phase2 Pass 3 converged, dmax= 1.881e-07, rmsbest= 8.736e-03, reclass= 791, unclass= 0 Starting pass 4 (of 25) of phase2 Pass 4 converged, dmax= 3.081e-07, rmsbest= 1.037e-03, reclass= 428, unclass= 0 Starting pass 5 (of 25) of phase2 Pass 5 converged, dmax= 5.816e-07, rmsbest= 7.097e-04, reclass= 109, unclass= 0 Starting pass 6 (of 25) of phase2 Phase2 passes converged because points are classified same as previous pass ==> Opening input journal file "/Users/jenkins/workspace/ESP_bPreBuilt/ESP126/EngSketchPad/data/Plugs/buildFinal.jrnl" ==> Closing input journal file ==> serveCSM completed successfully with no verification data real 0m32.412s user 0m46.668s sys 0m0.761s ++ set +x data/Plugs/plugs0d passed (as expected) -------------------------------------------------------------------------------------------------- [Execution node] check if [macys_VM] is in [[viggen]] Run condition [Execution node ] preventing perform for step [Execute shell] [Execution node] check if [macys_VM] is in [[windows10x64]] Run condition [Execution node ] preventing perform for step [Execute Windows batch command] [GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_bPreBuilt') [GNU C Compiler (gcc)] Successfully parsed console log [GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates) [GNU C Compiler (gcc)] Skipping post processing [GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues [GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_bPreBuilt') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_bPreBuilt') [Clang] Skipping post processing [Clang] No filter has been set, publishing all 0 issues [Clang] Repository miner is not configured, skipping repository mining [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_bPreBuilt') [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_bPreBuilt') [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Reference build recorder is not configured [Static Analysis] No valid reference build found [Static Analysis] All reported issues will be considered outstanding [Static Analysis] No quality gates have been set - skipping [Static Analysis] Health report is disabled - skipping [Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues) [Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_bPreBuilt/ESPVersion=126,buildnode=macys_VM #77'. [Checks API] No suitable checks publisher found. [WS-CLEANUP] Deleting project workspace... [WS-CLEANUP] Deferred wipeout is used... [WS-CLEANUP] done Finished: SUCCESS