touch /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/capsMode.so
rm /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/capsMode.so
g++-11 -m64 -g -fsanitize=undefined -fno-omit-frame-pointer -fuse-ld=gold -shared -Wl,-no-undefined -o /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/capsMode.so /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/obj/timCapsMode.o -L/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib -lcaps -locsm -lwsserver -legads -ldl -lm
gcc-11 -m64 -g -fsanitize=undefined -fno-omit-frame-pointer -fuse-ld=gold -c -O -fno-unit-at-a-time -fPIC -Wall -Wno-dangling-else -Wno-parentheses -Wno-unused-result -Wno-format-truncation -DREVISION=7.6 -I/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/include -I. timFlowchart.c -o /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/obj/timFlowchart.o
touch /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/flowchart.so
rm /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/flowchart.so
g++-11 -m64 -g -fsanitize=undefined -fno-omit-frame-pointer -fuse-ld=gold -shared -Wl,-no-undefined -o /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/flowchart.so /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/obj/timFlowchart.o -L/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib -lcaps -locsm -lwsserver -legads -ldl -lm
gcc-11 -m64 -g -fsanitize=undefined -fno-omit-frame-pointer -fuse-ld=gold -c -O -fno-unit-at-a-time -fPIC -Wall -Wno-dangling-else -Wno-parentheses -Wno-unused-result -Wno-format-truncation -DREVISION=7.6 -I/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/include -I. timViewer.c -o /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/obj/timViewer.o
touch /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/viewer.so
rm /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/viewer.so
g++-11 -m64 -g -fsanitize=undefined -fno-omit-frame-pointer -fuse-ld=gold -shared -Wl,-no-undefined -o /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/viewer.so /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/obj/timViewer.o -L/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib -lcaps -locsm -lwsserver -legads -ldl -lm
gcc-11 -m64 -g -fsanitize=undefined -fno-omit-frame-pointer -fuse-ld=gold -c -O -fno-unit-at-a-time -fPIC -Wall -Wno-dangling-else -Wno-parentheses -Wno-unused-result -Wno-format-truncation -DREVISION=7.6 -I/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/include -I. -I. -I/home/jenkins/util/ESP/Python/ESP_Python-3.9.13/include/python3.9 -I/home/jenkins/util/ESP/Python/ESP_Python-3.9.13/include/python3.9 timPyscript.c -o /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/obj/timPyscript.o
touch /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/pyscript.so
rm /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/pyscript.so
g++-11 -m64 -g -fsanitize=undefined -fno-omit-frame-pointer -fuse-ld=gold -shared -Wl,-no-undefined -o /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/pyscript.so /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/obj/timPyscript.o -L/home/jenkins/util/ESP/Python/ESP_Python-3.9.13/lib -lpython3.9 -lcrypt -lpthread -ldl -lutil -lm -lm -L/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib -lcaps -locsm -lwsserver -legads -ldl -lrt -Wl,-rpath /home/jenkins/util/ESP/Python/ESP_Python-3.9.13/lib
++ ln -f -s /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/OpenCSM/trunk/udc /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64
+++ find /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/OpenCSM/trunk/data/training/ -name Makefile
find: ‘/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/OpenCSM/trunk/data/training/’: No such file or directory
+ source /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/JenkinsESP/ESP_Sanitize.sh
++ '[' -z '' ']'
++ OUTLEVEL=0
++ mkdir -p /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/test
++ cd /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/test
++ [[ CAPS/AEROELASTIC =~ [0-9]+.[0-9]+ ]]
++ export ESPTEST=CAPS/AEROELASTIC
++ ESPTEST=CAPS/AEROELASTIC
++ [[ CAPS/AEROELASTIC == \C\A\P\S* ]]
++ export CAPSTARGET=AEROELASTIC
++ CAPSTARGET=AEROELASTIC
++ [[ AEROELASTIC == \u\n\i\t ]]
++ [[ AEROELASTIC == \t\r\a\i\n\i\n\g\2\0\1\8 ]]
++ [[ AEROELASTIC == \t\r\a\i\n\i\n\g ]]
++ [[ AEROELASTIC == *\_\o\f\f ]]
++ cd /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest
++ ./execute_CTestRegression.sh AEROELASTIC
Running.... AEROELASTIC c-Tests
=================================================
+ echo './aeroelasticSimple_Iterative_SU2_and_MystranTest test;'
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/cCAPSlog.txt
./aeroelasticSimple_Iterative_SU2_and_MystranTest test;
+ ./aeroelasticSimple_Iterative_SU2_and_MystranTest 0
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/cCAPSlog.txt
Attention: aeroelasticIterativeTest is hard coded to look for ../csmData/aeroelasticDataTransferSimple.csm
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
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 12793
Number of elements = 25582
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 25582
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 12793
Total number of elements = 25582
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Farfield, index = 1
Name = SymmPlane, index = 2
Name = Skin, index = 3
Number of surface: nodes - 12793, elements - 25582
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds: 1.23037
Creating surface mesh ...
Surface mesh seconds: 0.075587
Recovering boundaries...
Boundary recovery seconds: 0.174763
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds: 0.073086
Recovering Delaunayness...
Delaunay recovery seconds: 0.052488
Refining mesh...
17053 insertions, added 9952 points, 233965 tetrahedra in queue.
Refinement seconds: 2.4113
Smoothing vertices...
Mesh smoothing seconds: 2.41132
Improving mesh...
Mesh improvement seconds: 0.1618
Writing nodes.
Writing elements.
Writing faces.
Writing edges.
Output seconds: 0.028819
Total running seconds: 6.62114
Statistics:
Input points: 12793
Input facets: 25582
Input segments: 38373
Input holes: 0
Input regions: 0
Mesh points: 23155
Mesh tetrahedra: 101373
Mesh faces: 215537
Mesh faces on exterior boundary: 25582
Mesh faces on input facets: 25582
Mesh edges on input segments: 38373
Steiner points inside domain: 10362
Done meshing using TetGen!
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Skin
Boundary condition name - SymmPlane
Boundary condition name - Farfield
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 "BlackBird (7.4.0) "
Running SU2_CFD!
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 capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Skin, index = 1
Name = Rib_Root, index = 2
Creating FEA BEM
Mesh for body = 0
Number of nodal coordinates = 12
Number of elements = 20
Elemental Nodes = 0
Elemental Rods = 0
Elemental Tria3 = 20
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 - 2
Property name - Skin
No "material" specified for Property tuple Skin, defaulting to an index of 1
Property name - Rib_Root
No "material" specified for Property tuple Rib_Root, defaulting to an index of 1
Done getting FEA properties
Getting FEA constraints.......
Number of constraints - 1
Constraint name - edgeConstraint
No "constraintType" specified for ConstrNote: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
aint tuple edgeConstraint, defaulting to "ZeroDisplacement"
Done getting FEA constraints
Support tuple is NULL - No supports applied
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
Analysis tuple is NULL
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv
Number of variables = 13
Number of data points = 5887
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 3.116127e+09, tgt = 3.116127e+09, diff = 1.523180e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv
Number of variables = 13
Number of data points = 5887
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 3.053657e+09, tgt = 3.053657e+09, diff = 5.743027e-03
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv
Number of variables = 13
Number of data points = 5887
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 4.590485e+07, tgt = 4.590485e+07, diff = 0.000000e+00
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 8 (total = 8)
TransferName = Skin_Bottom
Number of Elements = 8 (total = 16)
TransferName = Skin_Tip
Number of Elements = 2 (total = 18)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Running mystran!
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
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 "BlackBird (7.4.0) "
Running SU2_DEF!
Running SU2_CFD!
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv
Number of variables = 13
Number of data points = 5887
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 3.116127e+09, tgt = 3.116127e+09, diff = 1.523180e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv
Number of variables = 13
Number of data points = 5887
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 3.053657e+09, tgt = 3.053657e+09, diff = 5.743027e-03
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv
Number of variables = 13
Number of data points = 5887
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 4.590485e+07, tgt = 4.590485e+07, diff = 0.000000e+00
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 8 (total = 8)
TransferName = Skin_Bottom
Number of Elements = 8 (total = 16)
TransferName = Skin_Tip
Number of Elements = 2 (total = 18)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Running mystran!
real 0m44.999s
user 0m41.152s
sys 0m3.443s
+ status=0
+ set +x
=============================================
CAPS verification (using c-executables) case ./aeroelasticSimple_Iterative_SU2_and_MystranTest passed (as expected)
=============================================
All tests pass!
++ '[' '!' -z ' -L/home/jenkins/util/ESP/Python/ESP_Python-3.9.13/lib -lpython3.9 -lcrypt -lpthread -ldl -lutil -lm -lm ' ']'
++ ./execute_PyTestRegression.sh AEROELASTIC
=================================================
Using python : /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/venv/bin/python
=================================================
Running.... AEROELASTIC PyTests
mystran: /home/jenkins/util/mystran/MYSTRAN/Binaries/mystran
=================================================
+ echo 'aeroelasticSimple_Pressure_SU2_and_Mystran.py test;'
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
aeroelasticSimple_Pressure_SU2_and_Mystran.py test;
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
+ python -u aeroelasticSimple_Pressure_SU2_and_Mystran.py -outLevel=0 -noPlotData
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
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 4929
Number of elements = 9854
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 9854
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 4929
Total number of elements = 9854
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Farfield, index = 1
Name = SymmPlane, index = 2
Name = Skin, index = 3
Number of surface: nodes - 4929, elements - 9854
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000QT1.00e-16A
Done meshing using TetGen!
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 (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
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: ../tetgen/tetgen_0.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_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Pressure_SM.
Volume file name: flow_aeroelasticSimple_Pressure_SM.
Restart file name: restart_flow_aeroelasticSimple_Pressure_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.
7509 grid points.
30226 volume elements.
3 surface markers.
100 boundary elements in index 0 (Marker = BC_1).
9640 boundary elements in index 1 (Marker = BC_2).
114 boundary elements in index 2 (Marker = BC_3).
30226 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: 45.4666. Mean K: 0.121675. Standard deviation K: 1.66704.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 19.0982| 84.1568|
| CV Face Area Aspect Ratio| 1.71143| 1527.78|
| CV Sub-Volume Ratio| 1| 5866.96|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 7509| 1/1.00| 10|
| 1| 1372| 1/5.47| 8.51168|
| 2| 276| 1/4.97| 7.48097|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 8.69203 m^2.
Area projection in the x-plane = 0.611023 m^2, y-plane = 0.284471 m^2, z-plane = 4.13497 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.378967 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.72584e-18 m, z-direction = -0.0445163 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
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 3.2056e-01| -0.535201| 1.762713| 1.447163| 4.933905| -1.247871|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.1485e-01| -0.597820| 1.787548| 1.659994| 4.852476| -1.064837|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.1432e-01| -0.765543| 1.728612| 1.627039| 4.680752| -0.454497|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.765543| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Pressure_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Pressure_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Pressure_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Pressure_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SM.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
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 ...... mystran
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 capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Skin, index = 1
Name = Rib_Root, index = 2
Creating FEA BEM
Getting quads for BEM!
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
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
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
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
Analysis tuple is NULL
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SM.csv
Number of variables = 13
Number of data points = 63
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 3.103461e+09, tgt = 3.103461e+09, diff = 2.820421e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SM.csv
Number of variables = 13
Number of data points = 63
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 3.011996e+09, tgt = 3.011996e+09, diff = 3.172831e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SM.csv
Number of variables = 13
Number of data points = 63
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 4.260421e+07, tgt = 4.260421e+07, diff = 1.692027e-05
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 81 (total = 81)
TransferName = Skin_Bottom
Number of Elements = 81 (total = 162)
TransferName = Skin_Tip
Number of Elements = 16 (total = 178)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Running Mystran......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Running PostAnalysis ...... mystran
real 0m14.221s
user 0m14.362s
sys 0m4.284s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Pressure_SU2_and_Mystran.py passed (as expected)
=================================================
=================================================
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
+ echo 'aeroelasticSimple_Displacement_SU2_and_Mystran.py test;'
aeroelasticSimple_Displacement_SU2_and_Mystran.py test;
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
+ python -u aeroelasticSimple_Displacement_SU2_and_Mystran.py -outLevel=0 -noPlotData
Running PreAnalysis ...... mystran
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 capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Skin, index = 1
Name = Rib_Root, index = 2
Creating FEA BEM
Getting quads for BEM!
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
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
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
Getting FEA loads.......
Number of loads - 1
Load name - pressureInternal
Done getting FEA loads
Analysis tuple is NULL
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Running Mystran......
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Running PostAnalysis ...... mystran
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
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 4929
Number of elements = 9854
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 9854
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 4929
Total number of elements = 9854
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Farfield, index = 1
Name = SymmPlane, index = 2
Name = Skin, index = 3
Number of surface: nodes - 4929, elements - 9854
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000QT1.00e-16A
Done meshing using TetGen!
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
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 180
Loading displacements for Subcase = 1
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Displacement_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Mesh Deformation Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../tetgen/tetgen_0.su2
---------------- Grid deformation parameters ( Zone 0 ) ----------------
Grid deformation using a linear elasticity method.
-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aeroelasticSimple_Displacement_SM.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.
7509 grid points.
30226 volume elements.
3 surface markers.
100 boundary elements in index 0 (Marker = BC_1).
9640 boundary elements in index 1 (Marker = BC_2).
114 boundary elements in index 2 (Marker = BC_3).
30226 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).
----------------------- Write deformed grid files -----------------------
|SU2 mesh |aeroelasticSimple_Displacement_SM.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.
------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.
Completed in 1.151313 seconds on 1 core.
------------------------- Exit Success (SU2_DEF) ------------------------
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
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: ../tetgen/tetgen_0.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_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Displacement_SM.
Volume file name: flow_aeroelasticSimple_Displacement_SM.
Restart file name: restart_flow_aeroelasticSimple_Displacement_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.
7509 grid points.
30226 volume elements.
3 surface markers.
100 boundary elements in index 0 (Marker = BC_1).
9640 boundary elements in index 1 (Marker = BC_2).
114 boundary elements in index 2 (Marker = BC_3).
30226 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: 45.4666. Mean K: 0.121675. Standard deviation K: 1.66704.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 19.0982| 84.1568|
| CV Face Area Aspect Ratio| 1.71143| 1527.78|
| CV Sub-Volume Ratio| 1| 5866.96|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 7509| 1/1.00| 10|
| 1| 1372| 1/5.47| 8.51168|
| 2| 276| 1/4.97| 7.48097|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 8.69203 m^2.
Area projection in the x-plane = 0.611023 m^2, y-plane = 0.284471 m^2, z-plane = 4.13497 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.378967 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.72584e-18 m, z-direction = -0.0445163 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
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 3.8240e-01| -0.535201| 1.762713| 1.447163| 4.933905| -1.247871|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.8629e-01| -0.597820| 1.787548| 1.659994| 4.852476| -1.064837|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.6442e-01| -0.765543| 1.728612| 1.627039| 4.680752| -0.454497|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.765543| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Displacement_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Displacement_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Displacement_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Displacement_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SM.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
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 0m19.102s
user 0m16.066s
sys 0m1.872s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Displacement_SU2_and_Mystran.py passed (as expected)
=================================================
=================================================
+ echo 'aeroelasticSimple_Iterative_SU2_and_Mystran.py test;'
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
aeroelasticSimple_Iterative_SU2_and_Mystran.py test;
+ python -u aeroelasticSimple_Iterative_SU2_and_Mystran.py -outLevel=0
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/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
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes = 3485
Number of elements = 6966
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 6966
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3485
Total number of elements = 6966
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Farfield, index = 1
Name = SymmPlane, index = 2
Name = Skin, index = 3
Number of surface: nodes - 3485, elements - 6966
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000QT1.00e-16A
Done meshing using TetGen!
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_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
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: ../tetgen/tetgen_0.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_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_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.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 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: 27.1257. Mean K: 0.0598259. Standard deviation K: 0.945506.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 12.6541| 83.7062|
| CV Face Area Aspect Ratio| 1.45416| 3253.37|
| CV Sub-Volume Ratio| 1| 2.23538e+32|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 5348| 1/1.00| 10|
| 1| 988| 1/5.41| 8.54305|
| 2| 177| 1/5.58| 7.22398|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 7.57417 m^2.
Area projection in the x-plane = 0.549259 m^2, y-plane = 0.226217 m^2, z-plane = 3.60855 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.37568 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.09713e-18 m, z-direction = -0.0342487 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
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 1.9346e-01| -0.348385| 1.966931| 1.613249| 5.120721| -1.717816|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.8755e-01| -0.442403| 2.014793| 1.899130| 5.021091| -1.860916|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.8789e-01| -0.571089| 1.888985| 2.017639| 4.890427| -1.771257|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.571089| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Iterative_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Iterative_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
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 capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Skin, index = 1
Name = Rib_Root, index = 2
Creating FEA BEM
Getting quads for BEM!
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
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
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
Analysis tuple is NULL
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 13
Number of data points = 25
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 3.109685e+09, tgt = 3.109685e+09, diff = 5.037911e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 13
Number of data points = 25
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 3.021395e+09, tgt = 3.021395e+09, diff = 5.733078e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 13
Number of data points = 25
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 3.789177e+07, tgt = 3.789177e+07, diff = 7.450581e-09
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 4 (total = 4)
TransferName = Skin_Bottom
Number of Elements = 4 (total = 8)
TransferName = Skin_Tip
Number of Elements = 2 (total = 10)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Mesh Deformation Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../tetgen/tetgen_0.su2
---------------- Grid deformation parameters ( Zone 0 ) ----------------
Grid deformation using a linear elasticity method.
-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aeroelasticSimple_Iterative_SM.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.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 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).
----------------------- Write deformed grid files -----------------------
|SU2 mesh |aeroelasticSimple_Iterative_SM.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.
------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.
Completed in 0.481647 seconds on 1 core.
------------------------- Exit Success (SU2_DEF) ------------------------
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
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: ../tetgen/tetgen_0.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_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_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.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 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: 27.1257. Mean K: 0.0598259. Standard deviation K: 0.945506.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 12.6541| 83.7062|
| CV Face Area Aspect Ratio| 1.45416| 3253.37|
| CV Sub-Volume Ratio| 1| 2.23538e+32|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 5348| 1/1.00| 10|
| 1| 988| 1/5.41| 8.54305|
| 2| 177| 1/5.58| 7.22398|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 7.57417 m^2.
Area projection in the x-plane = 0.549259 m^2, y-plane = 0.226217 m^2, z-plane = 3.60855 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.37568 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.09713e-18 m, z-direction = -0.0342487 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
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 1.5402e-01| -0.348385| 1.966931| 1.613249| 5.120721| -1.717816|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.5418e-01| -0.442403| 2.014793| 1.899130| 5.021091| -1.860916|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.5539e-01| -0.571089| 1.888985| 2.017639| 4.890427| -1.771257|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.571089| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Iterative_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Iterative_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
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_SM.csv
Number of variables = 13
Number of data points = 25
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 3.109685e+09, tgt = 3.109685e+09, diff = 5.037911e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 13
Number of data points = 25
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 3.021395e+09, tgt = 3.021395e+09, diff = 5.733078e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 13
Number of data points = 25
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 3.789177e+07, tgt = 3.789177e+07, diff = 7.450581e-09
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 4 (total = 4)
TransferName = Skin_Bottom
Number of Elements = 4 (total = 8)
TransferName = Skin_Tip
Number of Elements = 2 (total = 10)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Mesh Deformation Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../tetgen/tetgen_0.su2
---------------- Grid deformation parameters ( Zone 0 ) ----------------
Grid deformation using a linear elasticity method.
-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aeroelasticSimple_Iterative_SM.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.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 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).
----------------------- Write deformed grid files -----------------------
|SU2 mesh |aeroelasticSimple_Iterative_SM.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.
------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.
Completed in 0.440801 seconds on 1 core.
------------------------- Exit Success (SU2_DEF) ------------------------
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
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: ../tetgen/tetgen_0.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_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_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.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 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: 27.1257. Mean K: 0.0598259. Standard deviation K: 0.945506.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 12.6541| 83.7062|
| CV Face Area Aspect Ratio| 1.45416| 3253.37|
| CV Sub-Volume Ratio| 1| 2.23538e+32|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 5348| 1/1.00| 10|
| 1| 988| 1/5.41| 8.54305|
| 2| 177| 1/5.58| 7.22398|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 7.57417 m^2.
Area projection in the x-plane = 0.549259 m^2, y-plane = 0.226217 m^2, z-plane = 3.60855 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.37568 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.09713e-18 m, z-direction = -0.0342487 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
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 1.5804e-01| -0.348385| 1.966931| 1.613249| 5.120721| -1.717816|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.5694e-01| -0.442403| 2.014793| 1.899130| 5.021091| -1.860916|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.5673e-01| -0.571089| 1.888985| 2.017639| 4.890427| -1.771257|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.571089| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Iterative_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Iterative_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
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_SM.csv
Number of variables = 13
Number of data points = 25
CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure'
Rank 0: src = 3.109685e+09, tgt = 3.109685e+09, diff = 5.037911e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 13
Number of data points = 25
CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure'
Rank 0: src = 3.021395e+09, tgt = 3.021395e+09, diff = 5.733078e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative_SM.csv
Number of variables = 13
Number of data points = 25
CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure'
Rank 0: src = 3.789177e+07, tgt = 3.789177e+07, diff = 7.450581e-09
Extracting external pressure loads from data transfer....
TransferName = Skin_Top
Number of Elements = 4 (total = 4)
TransferName = Skin_Bottom
Number of Elements = 4 (total = 8)
TransferName = Skin_Tip
Number of Elements = 2 (total = 10)
Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file
Writing MYSTRAN instruction file....
Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Reading Mystran FO6 file - extracting Displacements!
Number of Grid Points = 12
Loading displacements for Subcase = 1
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticSimple_Iterative_SM_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Mesh Deformation Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../tetgen/tetgen_0.su2
---------------- Grid deformation parameters ( Zone 0 ) ----------------
Grid deformation using a linear elasticity method.
-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: aeroelasticSimple_Iterative_SM.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.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 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).
----------------------- Write deformed grid files -----------------------
|SU2 mesh |aeroelasticSimple_Iterative_SM.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.
------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.
Completed in 0.437237 seconds on 1 core.
------------------------- Exit Success (SU2_DEF) ------------------------
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2022, 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 <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
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: ../tetgen/tetgen_0.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_SM.dat.
Surface file name: surface_flow_aeroelasticSimple_Iterative_SM.
Volume file name: flow_aeroelasticSimple_Iterative_SM.
Restart file name: restart_flow_aeroelasticSimple_Iterative_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.
5348 grid points.
21576 volume elements.
3 surface markers.
34 boundary elements in index 0 (Marker = BC_1).
6890 boundary elements in index 1 (Marker = BC_2).
42 boundary elements in index 2 (Marker = BC_3).
21576 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: 27.1257. Mean K: 0.0598259. Standard deviation K: 0.945506.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 12.6541| 83.7062|
| CV Face Area Aspect Ratio| 1.45416| 3253.37|
| CV Sub-Volume Ratio| 1| 2.23538e+32|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 5348| 1/1.00| 10|
| 1| 988| 1/5.41| 8.54305|
| 2| 177| 1/5.58| 7.22398|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 7.57417 m^2.
Area projection in the x-plane = 0.549259 m^2, y-plane = 0.226217 m^2, z-plane = 3.60855 m^2.
Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.37568 m.
Min. coordinate in the x-direction = 0 m, y-direction = -2.09713e-18 m, z-direction = -0.0342487 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
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 1.5595e-01| -0.348385| 1.966931| 1.613249| 5.120721| -1.717816|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.5443e-01| -0.442403| 2.014793| 1.899130| 5.021091| -1.860916|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.6931e-01| -0.571089| 1.888985| 2.017639| 4.890427| -1.771257|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 3) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.571089| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_aeroelasticSimple_Iterative_SM.dat|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|CSV file |surface_flow_aeroelasticSimple_Iterative_SM.csv|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary |flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
|Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative_SM.szplt|
Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative_SM.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
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 = -0.371716
Cd = 0.20986
real 0m13.396s
user 0m12.665s
sys 0m5.854s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_SU2_and_Mystran.py passed (as expected)
=================================================
mystran: /home/jenkins/util/mystran/MYSTRAN/Binaries/mystran
flowCart: /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//flowCart
=================================================
+ echo 'aeroelasticSimple_Iterative_Cart3D_and_Mystran.py test;'
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
aeroelasticSimple_Iterative_Cart3D_and_Mystran.py test;
+ python -u aeroelasticSimple_Iterative_Cart3D_and_Mystran.py -outLevel=0
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = Skin, index = 1
Name = Rib_Root, index = 2
Body size = 4.649612
Tessellating body 1 with MaxEdge = 0.232481 Sag = 0.232481 Angle = 15.000000
Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 9 > autoInputs.out
Executing: ./aero.csh > aero.out
Sat Mar 11 12:39:02 AM EST 2023
-rwx------ 1 jenkins 77175 Mar 11 00:39 ./aero.csh
CART3D env variable set to: /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28
CART3D_ARCH env variable set to: X86_64_ICC
Using codes:
-rwxrwxr-x 1 jenkins 1705984 Oct 27 2020 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//cubes
-rwxrwxr-x 1 jenkins 1218584 Oct 27 2020 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//mgPrep
-rwxrwxr-x 1 jenkins 4873512 Oct 27 2020 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//flowCart
-rwxrwxr-x 1 jenkins 4627376 Oct 27 2020 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//xsensit
-rwxrwxr-x 1 jenkins 4947568 Oct 27 2020 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//adjointCart
-rwxrwxr-x 1 jenkins 20755448 Oct 27 2020 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//adjointErrorEst_quad
-rwxrwxr-x 1 jenkins 3470040 Oct 27 2020 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//adapt
md5sum checksums:
6ec5ce458d21d7844a77bdd24ec4cd67 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//cubes
eb35d7d79abba3dbf105aad946971d1e /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//mgPrep
3560020ad2308229a662deb02a126a10 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//flowCart
6c73f95283e601be7f1a6be74d0ee760 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//xsensit
adc935cc6d91afadc81adb04de12e7b0 /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//adjointCart
f4550d71f2590432be4d55787b0536de /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//adjointErrorEst_quad
706e383951182d9c8bc9f6393f50a31b /home/jenkins/util/cart3d/cart3d_v1.5.7_X86_64_ICC--20.10.28/bin/X86_64_ICC//adapt
Building initial mesh
ERROR: CUBES failed in /jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/pyCAPS/AeroelasticSimple_Iterative_Cart3D_Mystran/Scratch/cart3d/inputs/adapt00
===> ERROR: Cannot execute cubes -- please contact Cart3D developers.
Traceback (most recent call last):
File "/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/pyCAPS/aeroelasticSimple_Iterative_Cart3D_and_Mystran.py", line 136, in <module>
myProblem.analysis["cart3d"].runAnalysis()
File "/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/pyCAPS/pyCAPS/problem.py", line 2144, in runAnalysis
self._analysisObj.execute()
File "/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed
return func(*args, **kwargs)
File "/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 2900, in execute
if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs))
File "/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus
raise CAPSError(status, msg=msg, errors=errors)
pyCAPS.caps.CAPSError: CAPS_EXECERR:
================================================================================
================================================================================
real 0m10.215s
user 0m6.201s
sys 0m9.093s
+ status=1
+ set +x
=================================================
CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_Cart3D_and_Mystran.py failed (as NOT expected)
=================================================
*************************************************
*************************************************
=================================================
Did not run examples for:
Astros
=================================================
=================================================
Summary of examples NOT finished as expected
aeroelasticSimple_Iterative_Cart3D_and_Mystran.py
See pyCAPSlog.txt for more details.
=================================================
++ true
[GNU C Compiler (gcc)] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[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: '/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/LINUX64')
[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] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.6,CAPS/AEROELASTIC,LINUX64,reynolds)
[Static Analysis] Using reference build 'ESP_UndefinedCaps/CASREV=7.6,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=LINUX64,buildnode=reynolds #176' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1
[Static Analysis] -> All quality gates have been passed
[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_UndefinedCaps/CASREV=7.6,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=LINUX64,buildnode=reynolds #177'.
[Checks API] No suitable checks publisher found.
Build step 'Console output (build log) parsing' changed build result to FAILURE
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] Skipped based on build state FAILURE
Finished: FAILURE
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