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Full Log---------------------------------------- >>> alpha [-0.05149286] o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:50:25) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1 (22:50:29) aero.csh done o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s) >>> CL2 [2.59817062e-10] CL 1.612e-05 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:50:30) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1 (22:50:36) aero.csh done Max memory allowed: 32 GB Flow hexes: 2188 Estimated cutter memory: 0.000219 GB / DV Estimated xsensit memory: 0.004157 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (22:50:36) Linearizing cut-cells (22:50:36) ... done o Number of simultaneous xsensit jobs: 1 (22:50:36) Computing gradients (22:50:40) ... done o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s) >>> CL2_alpha [[2.03612433e-06]] ======================================== At iterate 3 f= 2.59817D-10 |proj g|= 2.03612D-06 ---------------------------------------- >>> alpha [-0.05176027] o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:50:41) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1 (22:50:45) aero.csh done o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s) >>> CL2 [9.25766089e-15] CL 1e-07 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:50:46) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1 (22:50:51) aero.csh done Max memory allowed: 32 GB Flow hexes: 2188 Estimated cutter memory: 0.000219 GB / DV Estimated xsensit memory: 0.004157 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (22:50:52) Linearizing cut-cells (22:50:52) ... done o Number of simultaneous xsensit jobs: 1 (22:50:52) Computing gradients (22:50:56) ... done o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s) >>> CL2_alpha [[1.21372408e-08]] ======================================== At iterate 4 f= 9.25766D-15 |proj g|= 1.21372D-08 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 1 4 5 4 0 0 1.214D-08 9.258D-15 F = 9.2576608860000000E-015 CONVERGENCE: NORM_OF_PROJECTED_GRADIENT_<=_PGTOL Optimization Complete ----------------------------------- Optimized value: [-0.05176027] real 1m42.628s user 0m58.597s sys 0m12.021s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case cart3d_OpenMDAO_3_alpha_PyTest.py passed (as expected) ================================================= ================================================= + echo 'cart3d_OpenMDAO_3_twist_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt cart3d_OpenMDAO_3_twist_PyTest.py test; + python -u cart3d_OpenMDAO_3_twist_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt ---------------------------------------- >>> twist [4.] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Getting CFD design variables....... Number of design variables - 1 Design Variable name - twist Done getting CFD design variables Getting CFD functional....... Number of design variables - 1 Objective name - CL2 Done getting CFD functional Body size = 3.630958 Tessellating body 1 with MaxEdge = 0.018155 Sag = 0.000908 Angle = 10.000000 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:50:59) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:51:23) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [0.00411365] CL 0.0641354 ---------------------------------------- ---------------------------------------- >>> twist [4.] >>> CL2 [0.00411365] CL 0.0641354 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:51:25) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:51:58) aero.csh done Max memory allowed: 32 GB Flow hexes: 37528 Estimated cutter memory: 0.003753 GB / DV Estimated xsensit memory: 0.071303 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (22:51:58) Linearizing cut-cells (22:52:00) ... done o Number of simultaneous xsensit jobs: 1 (22:52:00) Computing gradients (22:52:04) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[0.00210056]] ======================================== RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 1 M = 10 At X0 0 variables are exactly at the bounds At iterate 0 f= 4.11365D-03 |proj g|= 2.10056D-03 ---------------------------------------- >>> twist [3.99789944] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.630955 Tessellating body 1 with MaxEdge = 0.018155 Sag = 0.000908 Angle = 10.000000 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:52:06) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:52:32) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [0.0041123] CL 0.0641197 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:52:33) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:53:12) aero.csh done Max memory allowed: 32 GB Flow hexes: 37527 Estimated cutter memory: 0.003753 GB / DV Estimated xsensit memory: 0.071301 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (22:53:13) Linearizing cut-cells (22:53:15) ... done o Number of simultaneous xsensit jobs: 1 (22:53:15) Computing gradients (22:53:19) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[0.00210014]] ======================================== At iterate 1 f= 4.11230D-03 |proj g|= 2.10014D-03 ---------------------------------------- >>> twist [-6.51746271] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.635732 Tessellating body 1 with MaxEdge = 0.018179 Sag = 0.000909 Angle = 10.000000 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:53:21) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:53:43) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [0.00998113] CL -0.0999038 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:53:44) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:54:24) aero.csh done Max memory allowed: 32 GB Flow hexes: 37089 Estimated cutter memory: 0.003709 GB / DV Estimated xsensit memory: 0.070469 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (22:54:24) Linearizing cut-cells (22:54:26) ... done o Number of simultaneous xsensit jobs: 1 (22:54:26) Computing gradients (22:54:30) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[-0.00319688]] ======================================== ---------------------------------------- >>> twist [-0.14346246] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.625762 Tessellating body 1 with MaxEdge = 0.018129 Sag = 0.000906 Angle = 10.000000 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:54:33) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:54:51) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [4.79396149e-08] CL -0.00022338 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:54:52) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:55:25) aero.csh done Max memory allowed: 32 GB Flow hexes: 37755 Estimated cutter memory: 0.003776 GB / DV Estimated xsensit memory: 0.071735 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (22:55:25) Linearizing cut-cells (22:55:27) ... done o Number of simultaneous xsensit jobs: 1 (22:55:27) Computing gradients (22:55:31) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[-7.24741854e-06]] ======================================== At iterate 2 f= 4.79396D-08 |proj g|= 7.24742D-06 ---------------------------------------- >>> twist [-0.12922011] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.625747 Tessellating body 1 with MaxEdge = 0.018129 Sag = 0.000906 Angle = 10.000000 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7 -symmY -halfBody > autoInputs.out o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:55:34) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:56:01) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [2.18171674e-08] CL 0.00015117 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (22:56:02) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (22:56:35) aero.csh done Max memory allowed: 32 GB Flow hexes: 37755 Estimated cutter memory: 0.003776 GB / DV Estimated xsensit memory: 0.071735 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (22:56:35) Linearizing cut-cells (22:56:37) ... done o Number of simultaneous xsensit jobs: 1 (22:56:37) Computing gradients (22:56:41) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[4.89193111e-06]] ======================================== At iterate 3 f= 2.18172D-08 |proj g|= 4.89193D-06 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 1 3 5 3 0 0 4.892D-06 2.182D-08 F = 2.1817167420999998E-008 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- Optimized values: [-0.12922011] real 5m45.330s user 6m6.536s sys 0m20.283s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case cart3d_OpenMDAO_3_twist_PyTest.py passed (as expected) ================================================= ================================================= + echo 'fun3d_Morph_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt fun3d_Morph_PyTest.py test; + python -u fun3d_Morph_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.17.15 AFLR2 : Version Date 04/23/24 @ 12:51AM AFLR2 : Compile OS Darwin 23.4.0 arm64 AFLR2 : Compile Date 04/23/24 @ 12:51AM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.14 AFLR4 : Version Date 04/18/24 @ 12:45PM AFLR4 : Compile OS Darwin 23.4.0 arm64 AFLR4 : Compile Date 04/18/24 @ 03:04PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.8.0 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.8.0 EGADS : --------------------------------------- Volume mesh: Number of nodes = 82829 Number of elements = 483649 Number of triangles = 15680 Number of quadrilatarals = 0 Number of tetrahedrals = 467969 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Getting CFD design variables....... Number of design variables - 2 Design Variable name - Alpha Design Variable name - twist Done getting CFD design variables Getting CFD functional....... Number of design variables - 2 Objective name - Cd2 Objective name - Const Done getting CFD functional Python library was linked, but will not be used! Creating FUN3D directory tree DesignVariable = Alpha DesignVariable = twist Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1 Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1 Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1 Writing rubber.data Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Reading rubber.data Projecting tessellation 1 (of 3) on to new body Projecting tessellation 2 (of 3) on to new body Projecting tessellation 3 (of 3) on to new body Python library was linked, but will not be used! Creating FUN3D directory tree DesignVariable = Alpha DesignVariable = twist Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1 Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1 Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1 Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. Reading rubber.data real 0m11.146s user 0m8.103s sys 0m0.520s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case fun3d_Morph_PyTest.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Did not run examples for: Fun3D ================================================= All tests pass! ================================================= ================================================= ++ cd /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest ++ ./execute_PyTestRegression.sh CFD ================================================= Legacy Using python : /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/ESP/venv/bin/python ================================================= Running.... CFD PyTests ================================================= + rm -rf su2_and_AFLR2_NodeDist_PyTest + echo 'su2_and_AFLR2_NodeDist_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt su2_and_AFLR2_NodeDist_PyTest.py test; + python -u su2_and_AFLR2_NodeDist_PyTest.py -verbosity=0 -workDir=runDirectory + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.17.15 AFLR2 : Version Date 04/23/24 @ 12:51AM AFLR2 : Compile OS Darwin 23.4.0 arm64 AFLR2 : Compile Date 04/23/24 @ 12:51AM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 224 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 224 224 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 46 94 AFLR2 IG : Nodes, Faces = 92 186 AFLR2 IG : Nodes, Faces = 138 278 AFLR2 IG : Nodes, Faces = 184 370 AFLR2 IG : Nodes, Faces = 196 394 AFLR2 IG : Nodes, Faces = 224 450 AFLR2 IG : Nodes, Faces = 228 450 AFLR2 IG : Nodes, Faces = 224 224 AFLR2 : CPU Time = 0.001 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 224 224 AFLR2 GG : Nodes, Faces = 440 656 AFLR2 GG : Nodes, Faces = 649 1074 AFLR2 GG : Nodes, Faces = 853 1482 AFLR2 GG : Nodes, Faces = 1050 1876 AFLR2 GG : Nodes, Faces = 1238 2252 AFLR2 GG : Nodes, Faces = 1421 2618 AFLR2 GG : Nodes, Faces = 1594 2964 AFLR2 GG : Nodes, Faces = 1760 3296 AFLR2 GG : Nodes, Faces = 1915 3606 AFLR2 GG : Nodes, Faces = 2063 3902 AFLR2 GG : Nodes, Faces = 2202 4180 AFLR2 GG : Nodes, Faces = 2314 4404 AFLR2 GG : Nodes, Faces = 2423 4622 AFLR2 GG : Nodes, Faces = 2528 4832 AFLR2 GG : Nodes, Faces = 2634 5044 AFLR2 GG : Nodes, Faces = 2732 5240 AFLR2 GG : Nodes, Faces = 2831 5438 AFLR2 GG : Nodes, Faces = 2927 5630 AFLR2 GG : Nodes, Faces = 3018 5812 AFLR2 GG : Nodes, Faces = 3109 5994 AFLR2 GG : Nodes, Faces = 3202 6180 AFLR2 GG : Nodes, Faces = 3295 6366 AFLR2 GG : Nodes, Faces = 3386 6548 AFLR2 GG : Nodes, Faces = 3464 6704 AFLR2 GG : Nodes, Faces = 3535 6846 AFLR2 GG : Nodes, Faces = 3594 6964 AFLR2 GG : Nodes, Faces = 3639 7054 AFLR2 GG : Nodes, Faces = 3671 7118 AFLR2 GG : Nodes, Faces = 3691 7158 AFLR2 GG : Nodes, Faces = 3705 7186 AFLR2 GG : Nodes, Faces = 3712 7200 AFLR2 GG : Nodes, Faces = 3715 7206 AFLR2 : CPU Time = 0.005 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 3715 7206 AFLR2 : CPU Time = 0.001 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 3715 Number of elements = 7430 Number of tris = 7206 Number of quad = 0 Writing SU2 file .... SU2 expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: 0.4. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_5. Surface(s) plotted in the output file: BC_5, BC_2. Input mesh file name: ../runDirectory_SU2AFLR2NodeDistAnalysisTest1_aflr2AIM/aflr2_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_SU2_aflr2.dat. Surface file name: surface_flow_pyCAPS_SU2_aflr2. Volume file name: flow_pyCAPS_SU2_aflr2. Restart file name: restart_flow_pyCAPS_SU2_aflr2.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Inlet boundary| BC_4| +-----------------------------------------------------------------------+ | Outlet boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Two dimensional problem. 3715 grid points. 7206 volume elements. 4 surface markers. 98 boundary elements in index 0 (Marker = BC_2). 24 boundary elements in index 1 (Marker = BC_3). 24 boundary elements in index 2 (Marker = BC_4). 78 boundary elements in index 3 (Marker = BC_5). 7206 triangles. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 7206 TRIANGLE volume elements. There has been a re-orientation of 73 LINE surface elements. Identifying edges and vertices. Setting the control volume structure. Area of the computational grid: 999.917. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 177.06. Mean K: 1.97231. Standard deviation K: 13.0434. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 63.4343| 90| | CV Face Area Aspect Ratio| 1| 5.23543| | CV Sub-Volume Ratio| 1| 3.11804| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 3715| 1/1.00| 10| | 1| 1048| 1/3.54| 7.96696| | 2| 298| 1/3.52| 6.37252| +-------------------------------------------+ Finding max control volume width. Wetted area = 2.06136 m. Area projection in the x-plane = 0.178383 m, y-plane = 0.994925 m. Max. coordinate in the x-direction = 1 m, y-direction = 0.138389 m. Min. coordinate in the x-direction = -0.000250564 m, y-direction = -0.0151999 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_5 is NOT a single straight. Boundary marker BC_2 is NOT a single straight. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 216054| 1| m^2/s^2| 216054| | Velocity-X| 136.119| 1| m/s| 136.119| | Velocity-Y| 0| 1| m/s| 0| | Velocity Magnitude| 136.119| 1| m/s| 136.119| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.4| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 2.6921e-02| -0.385358| 2.453598| 1.625650| 5.369499| 0.360138| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.1573e-02| -0.512634| 2.087781| 1.374671| 4.973554| 1.183036| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.2426e-02| -0.792582| 1.733529| 1.142729| 4.657622| 3.896320| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.3167e-02| -0.880738| 1.486539| 1.023158| 4.334759| 14.592265| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.1903e-02| -0.987528| 1.351478| 0.932491| 4.191092| 111.166022| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 3.0704e-02| -1.104038| 1.188715| 0.874764| 3.951825| -483.924340| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 2.9418e-02| -1.178622| 1.124587| 0.844310| 3.820426| 127.331200| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 2.8663e-02| -1.243517| 1.097463| 0.824869| 3.768858| 40.162273| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 2.8297e-02| -1.287932| 1.075843| 0.810639| 3.733440| 25.154653| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 2.8032e-02| -1.300689| 1.046363| 0.775886| 3.684245| 21.097801| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.30069| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_pyCAPS_SU2_aflr2.dat | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). |CSV file |surface_flow_pyCAPS_SU2_aflr2.csv | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). |Tecplot binary |flow_pyCAPS_SU2_aflr2.szplt | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). |Tecplot binary surface |surface_flow_pyCAPS_SU2_aflr2.szplt| Error in tecFileWriterClose: Not all node map values for zone 1 have been written. Currently need 352 more values.0: Error finishing Tecplot file output. Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.650457 Cd = 0.030831 Cmz = 0.373226 Cx = 0.030831 Cy = 0.650457 Pressure Contribution Cl_p = 0.650457 Cd_p = 0.030831 Cmz_p = 0.373226 Cx_p = 0.030831 Cy_p = 0.650457 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.capsIntent' is deprecated. Please use 'None'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 0m1.477s user 0m1.260s sys 0m0.506s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case su2_and_AFLR2_NodeDist_PyTest.py passed (as expected) ================================================= ================================================= + rm -rf su2_and_AFLR2_PyTest + echo 'su2_and_AFLR2_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt su2_and_AFLR2_PyTest.py test; + python -u su2_and_AFLR2_PyTest.py -verbosity=0 -workDir=runDirectory + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Saving geometry Directory does not currently exist while creating a filename - it will be made automatically Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.17.15 AFLR2 : Version Date 04/23/24 @ 12:51AM AFLR2 : Compile OS Darwin 23.4.0 arm64 AFLR2 : Compile Date 04/23/24 @ 12:51AM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 545 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 545 545 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 110 222 AFLR2 IG : Nodes, Faces = 220 442 AFLR2 IG : Nodes, Faces = 330 662 AFLR2 IG : Nodes, Faces = 440 882 AFLR2 IG : Nodes, Faces = 517 1036 AFLR2 IG : Nodes, Faces = 545 1092 AFLR2 IG : Nodes, Faces = 549 1092 AFLR2 IG : Nodes, Faces = 545 545 AFLR2 : CPU Time = 0.002 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GGp: Nodes, Faces = 545 545 AFLR2 GGp: Nodes, Faces = 1083 1621 AFLR2 GGp: Nodes, Faces = 1616 2687 AFLR2 GGp: Nodes, Faces = 2144 3743 AFLR2 GGp: Nodes, Faces = 2661 4777 AFLR2 GGp: Nodes, Faces = 3171 5797 AFLR2 GGp: Nodes, Faces = 3672 6799 AFLR2 GGp: Nodes, Faces = 4158 7771 AFLR2 GGp: Nodes, Faces = 4653 8761 AFLR2 GGp: Nodes, Faces = 5142 9739 AFLR2 GGp: Nodes, Faces = 5608 10671 AFLR2 GGp: Nodes, Faces = 6055 11565 AFLR2 GGp: Nodes, Faces = 6482 12419 AFLR2 GGp: Nodes, Faces = 6880 13215 AFLR2 GGp: Nodes, Faces = 7257 13969 AFLR2 GGp: Nodes, Faces = 7614 14683 AFLR2 GGp: Nodes, Faces = 7947 15349 AFLR2 GGp: Nodes, Faces = 8276 16007 AFLR2 GGp: Nodes, Faces = 8575 16605 AFLR2 GGp: Nodes, Faces = 8869 17193 AFLR2 GGp: Nodes, Faces = 9140 17735 AFLR2 GGp: Nodes, Faces = 9401 18257 AFLR2 GGp: Nodes, Faces = 9654 18763 AFLR2 GGp: Nodes, Faces = 9887 19229 AFLR2 GGp: Nodes, Faces = 10110 19675 AFLR2 GGp: Nodes, Faces = 10315 20085 AFLR2 GGp: Nodes, Faces = 10497 20449 AFLR2 GGp: Nodes, Faces = 10656 20767 AFLR2 GGp: Nodes, Faces = 10791 21037 AFLR2 GGp: Nodes, Faces = 10919 21293 AFLR2 GGp: Nodes, Faces = 11022 21499 AFLR2 GGp: Nodes, Faces = 11092 21639 AFLR2 GGp: Nodes, Faces = 11145 21745 AFLR2 GGp: Nodes, Faces = 11156 21767 AFLR2 : CPU Time = 0.029 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 11156 21767 AFLR2 QI : Nodes, Faces = 11155 819 AFLR2 QI : Nodes, Faces = 11155 10473 AFLR2 QI : Nodes, Faces = 11155 21765 AFLR2 QI : Nodes, Faces = 11154 811 AFLR2 QI : Nodes, Faces = 11154 10476 AFLR2 QI : Nodes, Faces = 11154 21763 AFLR2 QI : Nodes, Faces = 11154 805 AFLR2 QI : Nodes, Faces = 11154 10479 AFLR2 QI : Nodes, Faces = 11154 21763 AFLR2 QI : Nodes, Faces = 11154 911 AFLR2 QI : Nodes, Faces = 11154 10426 AFLR2 QI : Nodes, Faces = 11154 21763 AFLR2 QI : Nodes, Faces = 11153 915 AFLR2 QI : Nodes, Faces = 11153 10423 AFLR2 QI : Nodes, Faces = 11153 917 AFLR2 QI : Nodes, Faces = 11153 10423 AFLR2 : CPU Time = 0.011 seconds AFLR2 : DONE EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)! EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)! Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 11153 Number of elements = 11885 Number of tris = 917 Number of quad = 10423 EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)! EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)! EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)! EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)! Writing Tecplot file .... Tecplot expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing Tecplot file Writing SU2 file .... SU2 expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: 0.4. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_5. Surface(s) plotted in the output file: BC_5, BC_2. Input mesh file name: ../runDirectory_SU2AFLR2ArbShapeAnalysisTest1_aflr2AIM/pyCAPS_su2_aflr2.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_su2_aflr2.dat. Surface file name: surface_flow_pyCAPS_su2_aflr2. Volume file name: flow_pyCAPS_su2_aflr2. Restart file name: restart_flow_pyCAPS_su2_aflr2.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Inlet boundary| BC_4| +-----------------------------------------------------------------------+ | Outlet boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Two dimensional problem. 11153 grid points. 11340 volume elements. 4 surface markers. 98 boundary elements in index 0 (Marker = BC_2). 24 boundary elements in index 1 (Marker = BC_3). 24 boundary elements in index 2 (Marker = BC_4). 399 boundary elements in index 3 (Marker = BC_5). 917 triangles. 10423 quadrilaterals. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 917 TRIANGLE volume elements. There has been a re-orientation of 10423 QUADRILATERAL volume elements. There has been a re-orientation of 73 LINE surface elements. Identifying edges and vertices. Setting the control volume structure. Area of the computational grid: 999.878. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 385.665. Mean K: 2.15881. Standard deviation K: 17.7215. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 49.3184| 90| | CV Face Area Aspect Ratio| 1.00035| 33.4982| | CV Sub-Volume Ratio| 1.00001| 7.89914| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11153| 1/1.00| 10| | 1| 2702| 1/4.13| 7.38309| | 2| 549| 1/4.92| 4.99198| +-------------------------------------------+ Finding max control volume width. Wetted area = 2.06265 m. Area projection in the x-plane = 0.211192 m, y-plane = 0.997011 m. Max. coordinate in the x-direction = 1 m, y-direction = 0.102037 m. Min. coordinate in the x-direction = 0.000323229 m, y-direction = -0.108492 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_5 is NOT a single straight. Boundary marker BC_2 is NOT a single straight. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 216054| 1| m^2/s^2| 216054| | Velocity-X| 136.119| 1| m/s| 136.119| | Velocity-Y| 0| 1| m/s| 0| | Velocity Magnitude| 136.119| 1| m/s| 136.119| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.4| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 7.6780e-02| 0.071067| 2.739763| 1.616077| 5.599701| 0.055267| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 7.5050e-02| -0.447576| 2.193837| 1.571349| 5.070382| 0.046028| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 7.9851e-02| -0.561159| 2.074597| 1.490746| 4.953698| 0.033910| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 7.8928e-02| -0.723326| 1.921155| 1.390756| 4.790278| 0.049695| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 7.8793e-02| -0.876572| 1.825653| 1.275093| 4.637161| 0.133976| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 8.0423e-02| -1.029177| 1.759196| 1.156078| 4.482282| 0.368542| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 7.9031e-02| -1.215334| 1.704909| 1.114966| 4.286060| 0.974759| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 7.8889e-02| -1.329970| 1.644937| 1.145030| 4.116982| 2.716332| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 7.8632e-02| -1.270672| 1.570739| 1.155400| 4.139480| 16.569216| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 7.9294e-02| -1.221243| 1.499646| 1.130319| 4.189559| -6.277653| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.22124| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_pyCAPS_su2_aflr2.dat | Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). |CSV file |surface_flow_pyCAPS_su2_aflr2.csv | Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). |Tecplot binary |flow_pyCAPS_su2_aflr2.szplt | Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). |Tecplot binary surface |surface_flow_pyCAPS_su2_aflr2.szplt| Error in tecFileWriterClose: Not all node map values for zone 1 have been written. Currently need 994 more values.0: Error finishing Tecplot file output. Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.072253 Cd = -0.01151 Cmz = 0.070975 Cx = -0.01151 Cy = 0.072253 Pressure Contribution Cl_p = 0.072253 Cd_p = -0.01151 Cmz_p = 0.070975 Cx_p = -0.01151 Cy_p = 0.072253 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.setGeometryVal' is deprecated. Please use 'Problem.geometry.despmtr["varname"].value'! WARNING: 'capsGeometry.saveGeometry' is deprecated. Please use 'Problem.geometry.save'! WARNING: 'capsProblem.capsIntent' is deprecated. Please use 'None'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 0m2.322s user 0m2.109s sys 0m0.717s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case su2_and_AFLR2_PyTest.py passed (as expected) ================================================= ================================================= + rm -rf su2_and_AFLR4_AFLR3_PyTest + echo 'su2_and_AFLR4_AFLR3_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt su2_and_AFLR4_AFLR3_PyTest.py test; + python -u su2_and_AFLR4_AFLR3_PyTest.py -verbosity=0 -workDir=runDirectory + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.17.15 AFLR2 : Version Date 04/23/24 @ 12:51AM AFLR2 : Compile OS Darwin 23.4.0 arm64 AFLR2 : Compile Date 04/23/24 @ 12:51AM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.14 AFLR4 : Version Date 04/18/24 @ 12:45PM AFLR4 : Compile OS Darwin 23.4.0 arm64 AFLR4 : Compile Date 04/18/24 @ 03:04PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.8.0 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.8.0 EGADS : --------------------------------------- Volume mesh: Number of nodes = 82815 Number of elements = 483153 Number of triangles = 15676 Number of quadrilatarals = 0 Number of tetrahedrals = 467477 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: 0.5901. Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 50 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 15.8114 m. Surface(s) where the force coefficients are evaluated and their reference origin for moment computation: - BC_1 (0, 0, 0). - BC_2 (0, 0, 0) m. Surface(s) plotted in the output file: BC_1, BC_2. Input mesh file name: ../runDirectory_SU2andAFRLMeshTest2_aflr3AIM/AFLR3_Mesh.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_su2AFLRTest.dat. Surface file name: surface_flow_su2AFLRTest. Volume file name: flow_su2AFLRTest. Restart file name: restart_flow_su2AFLRTest.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 82815 grid points. 467477 volume elements. 3 surface markers. 9898 boundary elements in index 0 (Marker = BC_1). 5358 boundary elements in index 1 (Marker = BC_2). 420 boundary elements in index 2 (Marker = BC_3). 467477 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.08667e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 4873.1. Mean K: 51.0385. Standard deviation K: 239.256. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 48.0933| 86.4301| | CV Face Area Aspect Ratio| 1.07283| 63.9477| | CV Sub-Volume Ratio| 1.04029| 465.158| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 82815| 1/1.00| 10| | 1| 13547| 1/6.11| 8.20357| | 2| 2052| 1/6.6| 6.55952| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.90569 m. Wetted area = 119.573 m^2. Area projection in the x-plane = 11.2425 m^2, y-plane = 5.04269 m^2, z-plane = 56.272 m^2. Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.583228 m. Min. coordinate in the x-direction = 0 m, y-direction = -7.90569 m, z-direction = -0.41192 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.8616e+00| -0.391291| 1.981254| 1.660524| 5.099605| 1.902032| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.9152e+00| -0.219350| 2.278737| 1.918311| 5.292022| 2.554664| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.9416e+00| -0.153479| 2.425136| 2.235353| 5.359194| 4.020266| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.9465e+00| -0.170970| 2.480546| 2.397595| 5.328161| 6.117324| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.9590e+00| -0.186611| 2.491207| 2.463546| 5.300426| 8.067452| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.186611| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_su2AFLRTest.dat | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |CSV file |surface_flow_su2AFLRTest.csv | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview |flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview surface |surface_flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.870415 Cd = 0.107892 Cmx = 0.000436 Cmy = -0.247989 Cmz = -0.000312 Cx = 0.092685 Cy = -0.000388 Cz = 0.872166 Pressure Contribution Cl_p = 0.870415 Cd_p = 0.107892 Cmx_p = 0.000436 Cmy_p = -0.247989 Cmz_p = -0.000312 Cx_p = 0.092685 Cy_p = -0.000388 Cz_p = 0.872166 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmx_v = 0.0 Cmy_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 Cz_v = 0.0 WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.setGeometryVal' is deprecated. Please use 'Problem.geometry.despmtr["varname"].value'! WARNING: 'capsGeometry.buildGeometry' is deprecated. Please use 'Problem.geometry.build'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 0m31.129s user 0m27.124s sys 0m1.028s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case su2_and_AFLR4_AFLR3_PyTest.py passed (as expected) ================================================= ================================================= + rm -rf su2_and_Delaundo_PyTest + echo 'su2_and_Delaundo_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt su2_and_Delaundo_PyTest.py test; + python -u su2_and_Delaundo_PyTest.py -verbosity=0 -workDir=runDirectory + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting edge discretization for body 1 Delaundo expects 2D meshes in the x-y plane... attempting to rotate mesh through node swapping! Swapping z and y coordinates! Writing delaundo control file - delaundo.ctr Writing out *.pts file Running Delaundo...... Reading delaundo mesh file - delaundoMesh.mesh Swapping y and z coordinates! Writing Tecplot file .... Tecplot expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing Tecplot file Writing SU2 file .... SU2 expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Warning: No boundary condition specified for capsGroup 2DSlice! Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: 0.4. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_5. Surface(s) plotted in the output file: BC_5, BC_2. Input mesh file name: ../runDirectory_SU2DelaundoAnalysisTest1_delaundoAIM/delaundoMesh.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_SU2_Delaundo.dat. Surface file name: surface_flow_pyCAPS_SU2_Delaundo. Volume file name: flow_pyCAPS_SU2_Delaundo. Restart file name: restart_flow_pyCAPS_SU2_Delaundo.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Inlet boundary| BC_4| +-----------------------------------------------------------------------+ | Outlet boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Two dimensional problem. 6317 grid points. 12340 volume elements. 5 surface markers. 24 boundary elements in index 0 (Marker = BC_2). 24 boundary elements in index 1 (Marker = BC_3). 24 boundary elements in index 2 (Marker = BC_2). 24 boundary elements in index 3 (Marker = BC_4). 198 boundary elements in index 4 (Marker = BC_5). 12340 triangles. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. There has been a re-orientation of 294 LINE surface elements. Identifying edges and vertices. Setting the control volume structure. Area of the computational grid: 999.917. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 1792.95. Mean K: 10.8142. Standard deviation K: 104.33. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 45.3524| 89.2595| | CV Face Area Aspect Ratio| 1.03245| 15.7138| | CV Sub-Volume Ratio| 1| 7.93643| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 6317| 1/1.00| 10| | 1| 1792| 1/3.53| 7.98923| | 2| 509| 1/3.52| 6.38684| +-------------------------------------------+ Finding max control volume width. Wetted area = 2.07206 m. Area projection in the x-plane = 0.179342 m, y-plane = 1.00053 m. Max. coordinate in the x-direction = 1 m, y-direction = 0.138492 m. Min. coordinate in the x-direction = -0.00104578 m, y-direction = -0.0151891 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_5 is NOT a single straight. Boundary marker BC_2 is a single straight. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 216054| 1| m^2/s^2| 216054| | Velocity-X| 136.119| 1| m/s| 136.119| | Velocity-Y| 0| 1| m/s| 0| | Velocity Magnitude| 136.119| 1| m/s| 136.119| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.4| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 5.5160e-02| -1.163068| 1.073873| 1.341547| 4.312268| 0.062082| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.9280e-02| -1.558471| 0.813117| 0.969484| 3.926501| 0.143132| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.7189e-02| -1.599269| 0.950037| 1.012154| 3.879885| 0.386300| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 5.7008e-02| -1.661284| 1.005970| 1.023067| 3.797319| 0.981260| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 5.8583e-02| -1.658421| 1.009907| 0.965279| 3.792658| 2.399755| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 5.7203e-02| -1.630602| 0.996801| 0.859556| 3.833204| 6.390579| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 5.8985e-02| -1.628009| 1.002770| 0.822847| 3.846297| 27.872536| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 5.7924e-02| -1.646113| 1.024424| 0.882502| 3.830202| -48.293527| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 5.7877e-02| -1.672152| 1.033657| 0.939200| 3.797228| -22.113788| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 5.7354e-02| -1.695131| 1.018255| 0.944150| 3.765919| -19.281368| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.69513| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_pyCAPS_SU2_Delaundo.dat| Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Delaundo.dat). |CSV file |surface_flow_pyCAPS_SU2_Delaundo.csv| Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Delaundo.dat). |Tecplot binary |flow_pyCAPS_SU2_Delaundo.szplt | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Delaundo.dat). |Tecplot binary surface |surface_flow_pyCAPS_SU2_Delaundo.szplt| Error in tecFileWriterClose: Not all node map values for zone 1 have been written. Currently need 492 more values.0: Error finishing Tecplot file output. Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Delaundo.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.805707 Cd = -0.041787 Cmz = 0.408515 Cx = -0.041787 Cy = 0.805707 Pressure Contribution Cl_p = 0.805707 Cd_p = -0.041787 Cmz_p = 0.408515 Cx_p = -0.041787 Cy_p = 0.805707 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 0m1.923s user 0m1.710s sys 0m0.468s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case su2_and_Delaundo_PyTest.py passed (as expected) ================================================= ================================================= + rm -rf su2_and_Tetgen_PyTest + echo 'su2_and_Tetgen_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt su2_and_Tetgen_PyTest.py test; + python -u su2_and_Tetgen_PyTest.py -verbosity=0 -workDir=runDirectory + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Getting surface mesh for body 1 (of 3) Getting surface mesh for body 2 (of 3) Getting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 2236 Number of elements = 4468 Number of triangle elements = 4468 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 636 Number of elements = 1268 Number of triangle elements = 1268 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 258 Number of elements = 512 Number of triangle elements = 512 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3130 Total number of elements = 6248 Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Farfield, index = 3 Number of surface: nodes - 3130, elements - 6248 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.022563 Creating surface mesh ... Surface mesh seconds: 0.001959 Recovering boundaries... Boundary recovery seconds: 0.051649 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.003307 Suppressing Steiner points ... Steiner suppression seconds: 6e-06 Recovering Delaunayness... Delaunay recovery seconds: 0.0062 Refining mesh... 4180 insertions, added 2142 points, 134947 tetrahedra in queue. 1391 insertions, added 431 points, 139550 tetrahedra in queue. 1855 insertions, added 477 points, 138154 tetrahedra in queue. 2472 insertions, added 613 points, 122807 tetrahedra in queue. 3296 insertions, added 507 points, 67228 tetrahedra in queue. 4393 insertions, added 431 points, 1310 tetrahedra in queue. Refinement seconds: 0.480834 Smoothing vertices... Mesh smoothing seconds: 0.303729 Improving mesh... Mesh improvement seconds: 0.008446 Jettisoning redundant points. Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.002723 Total running seconds: 0.881546 Statistics: Input points: 3130 Input facets: 6248 Input segments: 9372 Input holes: 2 Input regions: 0 Mesh points: 8227 Mesh tetrahedra: 40661 Mesh faces: 84447 Mesh faces on exterior boundary: 6250 Mesh faces on input facets: 6250 Mesh edges on input segments: 9373 Steiner points on input segments: 1 Steiner points inside domain: 5096 Done meshing using TetGen! Volume mesher did not preserve surface elements - data transfer will NOT be possible. Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: 0.5901. Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 50 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 15.8114 m. Surface(s) where the force coefficients are evaluated and their reference origin for moment computation: - BC_1 (0, 0, 0). - BC_2 (0, 0, 0) m. Surface(s) plotted in the output file: BC_1, BC_2. Input mesh file name: ../runDirectory_SU2TetgenAnalysisTest2_tetgenAIM/tetgen_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_SU2_Tetgen.dat. Surface file name: surface_flow_pyCAPS_SU2_Tetgen. Volume file name: flow_pyCAPS_SU2_Tetgen. Restart file name: restart_flow_pyCAPS_SU2_Tetgen.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 8227 grid points. 40661 volume elements. 3 surface markers. 4468 boundary elements in index 0 (Marker = BC_1). 1270 boundary elements in index 1 (Marker = BC_2). 512 boundary elements in index 2 (Marker = BC_3). 40661 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.08741e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 414.134. Mean K: 30.6158. Standard deviation K: 37.5195. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 2.25569| 83.562| | CV Face Area Aspect Ratio| 1.40614| 7154.17| | CV Sub-Volume Ratio| 1.02596| 261709| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 8227| 1/1.00| 10| | 1| 1360| 1/6.05| 8.23235| | 2| 235| 1/5.79| 6.87793| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.90569 m. Wetted area = 120.046 m^2. Area projection in the x-plane = 10.7914 m^2, y-plane = 4.5843 m^2, z-plane = 57.287 m^2. Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.557773 m. Min. coordinate in the x-direction = -0.00409054 m, y-direction = -7.90569 m, z-direction = -0.41192 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.4718e-01| 0.614349| 3.046325| 2.089422| 6.105244| 1.831854| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.4512e-01| 0.764583| 3.258604| 2.974732| 6.265552| 2.165840| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.5023e-01| 0.642409| 3.278261| 3.214494| 6.139447| 3.169947| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.5299e-01| 0.541917| 3.250446| 3.272037| 6.028748| 4.533401| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.5343e-01| 0.535101| 3.187480| 3.218588| 6.011712| 5.728616| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 0.535101| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_pyCAPS_SU2_Tetgen.dat | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat). |CSV file |surface_flow_pyCAPS_SU2_Tetgen.csv | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat). |Paraview |flow_pyCAPS_SU2_Tetgen.vtu | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat). |Paraview surface |surface_flow_pyCAPS_SU2_Tetgen.vtu | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.763097 Cd = 0.133208 Cmx = -0.004493 Cmy = -0.215511 Cmz = 0.000816 Cx = 0.11987 Cy = 0.0005 Cz = 0.765306 WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.setGeometryVal' is deprecated. Please use 'Problem.geometry.despmtr["varname"].value'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsAnalysis.aimName' is deprecated. Please use 'name'! WARNING: 'capsAnalysis.getAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 0m4.708s user 0m3.973s sys 0m0.445s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case su2_and_Tetgen_PyTest.py passed (as expected) ================================================= ================================================= + rm -rf su2_X43a_PyTest + echo 'su2_X43a_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt su2_X43a_PyTest.py test; + python -u su2_X43a_PyTest.py -verbosity=0 -workDir=runDirectory + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = x43A, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 3808 Number of elements = 7616 Number of triangle elements = 7616 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 5678 Number of elements = 11352 Number of triangle elements = 11352 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 9486 Total number of elements = 18968 Writing Tecplot file .... Finished writing Tecplot file No analysis directory provided - defaulting to altName Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = x43A, index = 1 Name = Farfield, index = 2 Number of surface: nodes - 9486, elements - 18968 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.040465 Creating surface mesh ... Surface mesh seconds: 0.00896 Recovering boundaries... Warning: 2 segments are not recovered. Boundary recovery seconds: 0.168341 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.010828 Suppressing Steiner points ... Steiner suppression seconds: 2.5e-05 Recovering Delaunayness... Delaunay recovery seconds: 0.02361 Refining mesh... 12647 insertions, added 5257 points, 11940 tetrahedra in queue. Refinement seconds: 0.502137 Smoothing vertices... Mesh smoothing seconds: 0.394646 Improving mesh... Mesh improvement seconds: 0.019689 Jettisoning redundant points. Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.00313 Total running seconds: 1.17223 Statistics: Input points: 9486 Input facets: 18968 Input segments: 28452 Input holes: 1 Input regions: 0 Mesh points: 14929 Mesh tetrahedra: 61505 Mesh faces: 132494 Mesh faces on exterior boundary: 18968 Mesh faces on input facets: 18968 Mesh edges on input segments: 28452 Steiner points inside domain: 5443 Done meshing using TetGen! Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - x43A Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: 3.5. Angle of attack (AoA): 3 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_1. Surface(s) plotted in the output file: BC_1. Input mesh file name: ../tetgenAIM_tetgenAIM/tetgen_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_x43a_Test.dat. Surface file name: surface_flow_x43a_Test. Volume file name: flow_x43a_Test. Restart file name: restart_flow_x43a_Test.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | Far-field| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 14929 grid points. 61505 volume elements. 2 surface markers. 7616 boundary elements in index 0 (Marker = BC_1). 11352 boundary elements in index 1 (Marker = BC_2). 61505 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.67745e+08. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 95.6599. Mean K: 0.523696. Standard deviation K: 2.57688. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 2.01085| 85.2046| | CV Face Area Aspect Ratio| 1.41431| 3475.64| | CV Sub-Volume Ratio| 1| 768690| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 14929| 1/1.00| 10| | 1| 2715| 1/5.5| 8.49841| | 2| 490| 1/5.54| 7.20395| +-------------------------------------------+ Finding max control volume width. Semi-span length = 30 m. Wetted area = 13596.3 m^2. Area projection in the x-plane = 761.676 m^2, y-plane = 2062.27 m^2, z-plane = 5463.61 m^2. Max. coordinate in the x-direction = 150 m, y-direction = 30 m, z-direction = 19 m. Min. coordinate in the x-direction = 0 m, y-direction = -30 m, z-direction = -10.3 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 916077| 1| m^2/s^2| 916077| | Velocity-X| 1189.41| 1| m/s| 1189.41| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 62.3342| 1| m/s| 62.3342| | Velocity Magnitude| 1191.04| 1| m/s| 1191.04| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 3.5| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.2049e-01| 2.730238| 5.664282| 4.727966| 8.729713| -0.338259| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.0462e-01| 3.172855| 6.235351| 5.708733| 9.163474| -0.117122| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.8731e-01| 3.313832| 6.405575| 5.809826| 9.273948| -0.036095| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 2.8906e-01| 3.301504| 6.396712| 5.682129| 9.288613| -0.015822| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.8867e-01| 3.134853| 6.203812| 5.540269| 9.119715| -0.030764| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 3.13485| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_x43a_Test.dat | Writing the forces breakdown file (forces_breakdown_x43a_Test.dat). |CSV file |surface_flow_x43a_Test.csv | Writing the forces breakdown file (forces_breakdown_x43a_Test.dat). |Paraview |flow_x43a_Test.vtu | Writing the forces breakdown file (forces_breakdown_x43a_Test.dat). |Paraview surface |surface_flow_x43a_Test.vtu | Writing the forces breakdown file (forces_breakdown_x43a_Test.dat). +-----------------------------------------------------------------------+ Warning: there are 124 non-physical points in the solution. Warning: 58 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = -3.688941 Cd = 119.911192 Cmx = 35.034239 Cmy = 8986.683762 Cmz = 192.445678 Cx = 119.939922 Cy = 1.734147 Cz = 2.591782 WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.capsIntent' is deprecated. Please use 'None'! WARNING: 'capsGeometry.setGeometryVal' is deprecated. Please use 'Problem.geometry.despmtr["varname"].value'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsAnalysis.aimName' is deprecated. Please use 'name'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 0m8.726s user 0m9.435s sys 0m0.808s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case su2_X43a_PyTest.py passed (as expected) ================================================= ./execute_PyTestRegression.sh: line 304: ulimit: stack size: cannot modify limit: Operation not permitted ================================================= + rm -rf cart_PyTest + echo 'cart_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt cart_PyTest.py test; + python -u cart_PyTest.py -verbosity=0 -workDir=runDirectory + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Loading AIM Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 7.674092 Tessellating body 1 with MaxEdge = 0.191852 Sag = 0.007674 Angle = 15.000000 Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 12 > autoInputs.out Running CART3D C_A 0.1122804 C_Y 0.0048773067 C_N -0.00061625638 C_D 0.11219049 C_S 0.0048773067 C_L -0.0045344104 C_l 0.000748749 C_m 0.000234329 C_n 0.244515 C_M_x 0.00928175 C_M_y 0.000234329 C_M_z 0.24434 WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 2m8.531s user 3m19.314s sys 0m3.609s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case cart_PyTest.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Legacy Did not run examples for: Fun3D ================================================= All tests pass! ================================================= ================================================= [Execution node] check if [viggen] is in [[windows10x64]] Run condition [Execution node ] preventing perform for step [Execute Windows batch command] [GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64') [GNU C Compiler (gcc)] Successfully parsed console log [GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates) [GNU C Compiler (gcc)] Skipping post processing [GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues [GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Successfully parsed console log [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64') [Clang] Skipping post processing [Clang] No filter has been set, publishing all 0 issues [Clang] Repository miner is not configured, skipping repository mining [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64') [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: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/CFD/DARWIN_ARM64') [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Reference build recorder is not configured [Static Analysis] No valid reference build found [Static Analysis] All reported issues will be considered outstanding [Static Analysis] No quality gates have been set - skipping [Static Analysis] Health report is disabled - skipping [Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues) [Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_RegCaps/CASREV=7.8,ESPTEST=CAPS/CFD,ESP_ARCH=DARWIN_ARM64,buildnode=viggen #644'. [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