The Jenkins Controller is preparing for shutdown. No new builds can be started.
Skipping 445 KB.. Full Logtouch /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/pyscript.so rm /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/pyscript.so g++-11 -g -fsanitize=undefined -fno-omit-frame-pointer -fuse-ld=gold -shared -Wl,-no-undefined -o /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/lib/pyscript.so /jenkins/workspace/ESP_UndefinedCaps/7.4/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/7.4/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/7.4/CAPS/AEROELASTIC/LINUX64/OpenCSM/trunk/udc /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64 +++ find /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/OpenCSM/trunk/data/training/ -name Makefile find: ‘/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/OpenCSM/trunk/data/training/’: No such file or directory + source /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/JenkinsESP/ESP_Sanitize.sh ++ '[' -z '' ']' ++ OUTLEVEL=0 ++ mkdir -p /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/ESP/test ++ cd /jenkins/workspace/ESP_UndefinedCaps/7.4/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/7.4/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/7.4/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/7.4/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: 1.45811 Creating surface mesh ... Surface mesh seconds: 0.076919 Recovering boundaries... Boundary recovery seconds: 0.235419 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.084408 Recovering Delaunayness... Delaunay recovery seconds: 0.074031 Refining mesh... 17053 insertions, added 9952 points, 233965 tetrahedra in queue. Refinement seconds: 2.38694 Smoothing vertices... Mesh smoothing seconds: 3.1563 Improving mesh... Mesh improvement seconds: 0.246863 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.034526 Total running seconds: 7.75562 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 ConsNote: 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 traint 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 0m45.825s user 0m41.162s sys 0m2.995s + 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/7.4/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/7.4/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt aeroelasticSimple_Pressure_SU2_and_Mystran.py test; + python -u aeroelasticSimple_Pressure_SU2_and_Mystran.py -outLevel=0 -noPlotData + tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/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 = 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| 2.8384e-01| -0.535201| 1.762713| 1.447163| 4.933905| -1.247871| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.2237e-01| -0.597820| 1.787548| 1.659994| 4.852476| -1.064837| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.0755e-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 0m17.265s user 0m14.519s sys 0m1.002s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelasticSimple_Pressure_SU2_and_Mystran.py passed (as expected) ================================================= ================================================= + echo 'aeroelasticSimple_Displacement_SU2_and_Mystran.py test;' + tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt aeroelasticSimple_Displacement_SU2_and_Mystran.py test; + python -u aeroelasticSimple_Displacement_SU2_and_Mystran.py -outLevel=0 -noPlotData + tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64/ESP/LINUX64/examples/regressionTest/pyCAPSlog.txt 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 1.284086 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| 3.4281e-01| -0.535201| 1.762713| 1.447163| 4.933905| -1.247871| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.3775e-01| -0.597820| 1.787548| 1.659994| 4.852476| -1.064837| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.5597e-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 0m15.733s user 0m13.436s sys 0m1.535s + 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/7.4/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/7.4/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| 2.3983e-01| -0.348385| 1.966931| 1.613249| 5.120721| -1.717816| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.1110e-01| -0.442403| 2.014793| 1.899130| 5.021091| -1.860916| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.1734e-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 0.647027 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| 2.2757e-01| -0.348385| 1.966931| 1.613249| 5.120721| -1.717816| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.3234e-01| -0.442403| 2.014793| 1.899130| 5.021091| -1.860916| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.3844e-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 0.551911 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| 2.0555e-01| -0.348385| 1.966931| 1.613249| 5.120721| -1.717816| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.0323e-01| -0.442403| 2.014793| 1.899130| 5.021091| -1.860916| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.0369e-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 0.533295 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| 2.1121e-01| -0.348385| 1.966931| 1.613249| 5.120721| -1.717816| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.1256e-01| -0.442403| 2.014793| 1.899130| 5.021091| -1.860916| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.1224e-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 0m20.024s user 0m14.672s sys 0m2.607s + 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_v1.5.9_X86_64_ICC--22.11.16/bin/X86_64_ICC//flowCart ================================================= + echo 'aeroelasticSimple_Iterative_Cart3D_and_Mystran.py test;' + tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/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/7.4/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 Cl = 0.11555834 Cd = 0.06178034 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 = 145 Number of elements = 160 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 34 Elemental Quad4 = 126 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 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 2.207283e+04, tgt = 2.207283e+04, diff = 1.422874e-03 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 2.166467e+04, tgt = 2.166467e+04, diff = 1.604394e-03 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 3.226356e+02, tgt = 3.226356e+02, diff = 1.270223e-08 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 63 (total = 63) TransferName = Skin_Bottom Number of Elements = 63 (total = 126) TransferName = Skin_Tip Number of Elements = 12 (total = 138) 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 = 145 Loading displacements for Subcase = 1 Reading Mystran FO6 file - extracting Displacements! Number of Grid Points = 145 Loading displacements for Subcase = 1 Reading Mystran FO6 file - extracting Displacements! Number of Grid Points = 145 Loading displacements for Subcase = 1 Executing: ./aero.csh > aero.out Cl = 0.11694301 Cd = 0.06409767 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 2.204741e+04, tgt = 2.204741e+04, diff = 1.401637e-03 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 2.164565e+04, tgt = 2.164564e+04, diff = 2.979999e-03 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 3.221797e+02, tgt = 3.221797e+02, diff = 1.021664e-08 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 63 (total = 63) TransferName = Skin_Bottom Number of Elements = 63 (total = 126) TransferName = Skin_Tip Number of Elements = 12 (total = 138) 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 = 145 Loading displacements for Subcase = 1 Reading Mystran FO6 file - extracting Displacements! Number of Grid Points = 145 Loading displacements for Subcase = 1 Reading Mystran FO6 file - extracting Displacements! Number of Grid Points = 145 Loading displacements for Subcase = 1 Executing: ./aero.csh > aero.out Cl = 0.11789958 Cd = 0.064176885 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 2.204717e+04, tgt = 2.204717e+04, diff = 1.417227e-03 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 2.164767e+04, tgt = 2.164766e+04, diff = 1.527730e-03 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 3.219928e+02, tgt = 3.219928e+02, diff = 5.713389e-09 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 63 (total = 63) TransferName = Skin_Bottom Number of Elements = 63 (total = 126) TransferName = Skin_Tip Number of Elements = 12 (total = 138) 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 = 145 Loading displacements for Subcase = 1 Reading Mystran FO6 file - extracting Displacements! Number of Grid Points = 145 Loading displacements for Subcase = 1 Reading Mystran FO6 file - extracting Displacements! Number of Grid Points = 145 Loading displacements for Subcase = 1 Executing: ./aero.csh > aero.out Cl = 0.11822931 Cd = 0.064272003 real 1m57.566s user 2m56.907s sys 0m36.395s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_Cart3D_and_Mystran.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Did not run examples for: Astros ================================================= All tests pass! [GNU C Compiler (gcc)] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/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/7.4/CAPS/AEROELASTIC/LINUX64') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/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/7.4/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] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64') [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/AEROELASTIC/LINUX64') [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Reference build recorder is not configured [Static Analysis] Obtaining reference build from same job (7.4,CAPS/AEROELASTIC,LINUX64,reynolds) [Static Analysis] Using reference build 'ESP_UndefinedCaps/CASREV=7.4,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=7.4,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=LINUX64,buildnode=reynolds #178'. [Checks API] No suitable checks publisher found. [PostBuildScript] - [INFO] Executing post build scripts. [PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX [WS-CLEANUP] Deleting project workspace... [WS-CLEANUP] done Finished: SUCCESS