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Full Log| 0| 0| 9| 0.0000e+00| 0.0000e+00| 7.5071e-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 real 0m3.047s user 0m2.534s sys 0m1.289s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_AFLR2_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_and_AFLR4_AFLR3_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt su2_and_AFLR4_AFLR3_PyTest.py test; + python -u su2_and_AFLR4_AFLR3_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.17.15 AFLR2 : Version Date 04/23/24 @ 12:51AM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 04/23/24 @ 11:49AM 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 x86_64 AFLR4 : Compile Date 04/23/24 @ 11:49AM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.7.0 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.7.0 EGADS : --------------------------------------- Volume mesh: Number of nodes = 39312 Number of elements = 226864 Number of triangles = 12446 Number of quadrilatarals = 0 Number of tetrahedrals = 214418 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wake Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "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: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-8. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_su2AFLRTest.dat. Surface file name: surface_flow_su2AFLRTest. Volume file name: flow_su2AFLRTest. Restart file name: restart_flow_su2AFLRTest.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_4| +-----------------------------------------------------------------------+ | Internal boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 39312 grid points. 214418 volume elements. 4 surface markers. 6594 boundary elements in index 0 (Marker = BC_1). 5358 boundary elements in index 1 (Marker = BC_2). 74 boundary elements in index 2 (Marker = BC_3). 420 boundary elements in index 3 (Marker = BC_4). 214418 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.08667e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 4873.1. Mean K: 61.8682. Standard deviation K: 266.942. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 17.1608| 84.739| | CV Face Area Aspect Ratio| 1.11815| 37015.5| | CV Sub-Volume Ratio| 1.04044| 455686| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 39312| 1/1.00| 10| | 1| 6485| 1/6.06| 8.22658| | 2| 1015| 1/6.39| 6.65012| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.90569 m. Wetted area = 118.038 m^2. Area projection in the x-plane = 11.1419 m^2, y-plane = 4.96714 m^2, z-plane = 55.4182 m^2. Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.582636 m. Min. coordinate in the x-direction = 0 m, y-direction = -7.90569 m, z-direction = -0.41192 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 9.5056e-01| -0.064586| 2.297676| 2.033300| 5.426310| 1.967108| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 9.2434e-01| -0.028142| 2.443813| 2.177084| 5.469820| 2.669025| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 9.0807e-01| 0.006388| 2.521945| 2.416533| 5.497519| 4.072698| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 9.1313e-01| -0.032771| 2.543134| 2.541766| 5.444377| 5.959388| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 9.0903e-01| -0.059484| 2.561671| 2.593774| 5.414288| 7.593451| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 9.0031e-01| -0.076814| 2.565225| 2.615896| 5.407625| 8.782803| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 9.1315e-01| -0.111978| 2.544207| 2.636258| 5.381265| 9.653546| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 9.2783e-01| -0.156369| 2.495539| 2.651467| 5.333878| 10.185394| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 9.2723e-01| -0.203072| 2.428150| 2.650114| 5.275471| 10.322264| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 9.2356e-01| -0.251896| 2.375012| 2.624886| 5.221589| 10.161308| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.251896| < -8| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_su2AFLRTest.dat | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |CSV file |surface_flow_su2AFLRTest.csv | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview |flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview surface |surface_flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.796713 Cd = 0.078407 Cmx = 0.000211 Cmy = -0.204659 Cmz = 0.000288 Cx = 0.06449 Cy = 0.000454 Cz = 0.79796 Pressure Contribution Cl_p = 0.796713 Cd_p = 0.078407 Cmx_p = 0.000211 Cmy_p = -0.204659 Cmz_p = 0.000288 Cx_p = 0.06449 Cy_p = 0.000454 Cz_p = 0.79796 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmx_v = 0.0 Cmy_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 Cz_v = 0.0 real 0m34.596s user 0m32.559s sys 0m1.437s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_AFLR4_AFLR3_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_Morph_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt su2_Morph_PyTest.py test; + python -u su2_Morph_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 AFLR4 : Proximity BG Surface Grid Generation Skipped AFLR4 : No Modifications Required Writing Tecplot file .... Finished writing Tecplot file Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = Wing1, index = 1 Name = Wing2, index = 2 Name = Wake, index = 3 Name = Farfield, index = 4 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.17.15 AFLR2 : Version Date 04/23/24 @ 12:51AM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 04/23/24 @ 11:49AM 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 x86_64 AFLR4 : Compile Date 04/23/24 @ 11:49AM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.7.0 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.7.0 EGADS : --------------------------------------- Volume mesh: Number of nodes = 56062 Number of elements = 324627 Number of triangles = 15872 Number of quadrilatarals = 0 Number of tetrahedrals = 308755 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing Tecplot file .... Finished writing Tecplot file Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wake Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Writing SU2 surface file Writing SU2 Motion File - su2AFLRTest_motion.dat Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 15 - bcProps.surfaceProp[2].surfaceType = 1 - bcProps.surfaceProp[3].surfaceType = 1 Done boundary flags Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "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 40 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 14.1421 m. Surface(s) where the force coefficients are evaluated and their reference origin for moment computation: - BC_1 (0, 0, 0). - BC_2 (0, 0, 0) m. Surface(s) plotted in the output file: BC_1, BC_2. Surface(s) affected by the design variables: BC_1, BC_2. Input mesh file name: ../volumeMesh/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-8. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_su2AFLRTest.dat. Surface file name: surface_flow_su2AFLRTest. Volume file name: flow_su2AFLRTest. Restart file name: restart_flow_su2AFLRTest.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_4| +-----------------------------------------------------------------------+ | Internal boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 56062 grid points. 308755 volume elements. 4 surface markers. 9958 boundary elements in index 0 (Marker = BC_1). 5414 boundary elements in index 1 (Marker = BC_2). 80 boundary elements in index 2 (Marker = BC_3). 420 boundary elements in index 3 (Marker = BC_4). 308755 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.08667e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 5523.74. Mean K: 58.8177. Standard deviation K: 282.533. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 25.8353| 86.1799| | CV Face Area Aspect Ratio| 1.02126| 47603.8| | CV Sub-Volume Ratio| 1.04989| 165826| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 56062| 1/1.00| 10| | 1| 9228| 1/6.08| 8.22061| | 2| 1406| 1/6.56| 6.586| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.07107 m. Wetted area = 96.2324 m^2. Area projection in the x-plane = 7.65774 m^2, y-plane = 4.21853 m^2, z-plane = 45.5887 m^2. Max. coordinate in the x-direction = 12.3872 m, y-direction = 7.07107 m, z-direction = 0.521791 m. Min. coordinate in the x-direction = 0 m, y-direction = -7.07107 m, z-direction = -0.0650201 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.2799e+00| -0.457870| 1.873279| 1.656710| 5.033025| 0.755651| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.2814e+00| -0.472284| 2.010746| 1.748231| 5.024932| 1.425370| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.2760e+00| -0.414217| 2.107665| 1.963200| 5.074925| 3.245288| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.2762e+00| -0.400337| 2.167522| 2.099318| 5.078948| 7.034217| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.2944e+00| -0.401529| 2.203755| 2.175567| 5.071313| 12.883621| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.3093e+00| -0.407291| 2.221380| 2.217144| 5.067540| 20.159074| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.3188e+00| -0.411436| 2.211548| 2.246056| 5.067163| 27.796880| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.3276e+00| -0.418757| 2.160924| 2.267618| 5.055632| 32.034412| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.3530e+00| -0.438528| 2.092229| 2.272883| 5.027335| 30.335774| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.3777e+00| -0.487870| 2.016953| 2.255847| 4.971131| 25.705102| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.48787| < -8| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_su2AFLRTest.dat | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |CSV file |surface_flow_su2AFLRTest.csv | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview |flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview surface |surface_flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.52174 Cd = 0.020297 Projecting tessellation 1 (of 4) on to new body Projecting tessellation 2 (of 4) on to new body Projecting tessellation 3 (of 4) on to new body Projecting tessellation 4 (of 4) on to new body Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wake Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Writing SU2 surface file Writing SU2 Motion File - su2AFLRTest_motion.dat Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 15 - bcProps.surfaceProp[2].surfaceType = 1 - bcProps.surfaceProp[3].surfaceType = 1 Done boundary flags Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Mesh Morphing...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: aflr3_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_4| +-----------------------------------------------------------------------+ | Internal boundary| BC_3| +-----------------------------------------------------------------------+ Three dimensional problem. 56062 grid points. 308755 volume elements. 4 surface markers. 9958 boundary elements in index 0 (Marker = BC_1). 5414 boundary elements in index 1 (Marker = BC_2). 80 boundary elements in index 2 (Marker = BC_3). 420 boundary elements in index 3 (Marker = BC_4). 308755 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 2.08667e+06. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Ignoring Convergence Field(s): RMS_DENSITY Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 11.848600 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Paraview |volume_deformed.vtu | |Paraview surface |surface_deformed.vtu | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "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 40 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 14.1421 m. Surface(s) where the force coefficients are evaluated and their reference origin for moment computation: - BC_1 (0, 0, 0). - BC_2 (0, 0, 0) m. Surface(s) plotted in the output file: BC_1, BC_2. Surface(s) affected by the design variables: BC_1, BC_2. Input mesh file name: aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-8. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_su2AFLRTest.dat. Surface file name: surface_flow_su2AFLRTest. Volume file name: flow_su2AFLRTest. Restart file name: restart_flow_su2AFLRTest.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_4| +-----------------------------------------------------------------------+ | Internal boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 56062 grid points. 308755 volume elements. 4 surface markers. 9958 boundary elements in index 0 (Marker = BC_1). 5414 boundary elements in index 1 (Marker = BC_2). 80 boundary elements in index 2 (Marker = BC_3). 420 boundary elements in index 3 (Marker = BC_4). 308755 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.08667e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 5523.56. Mean K: 58.7619. Standard deviation K: 282.437. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 17.0659| 85.7425| | CV Face Area Aspect Ratio| 1.02723| 55937.4| | CV Sub-Volume Ratio| 1.05439| 215979| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 56062| 1/1.00| 10| | 1| 9228| 1/6.08| 8.22061| | 2| 1406| 1/6.56| 6.586| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.07107 m. Wetted area = 95.6308 m^2. Area projection in the x-plane = 9.17945 m^2, y-plane = 4.04295 m^2, z-plane = 44.962 m^2. Max. coordinate in the x-direction = 12.3585 m, y-direction = 7.07107 m, z-direction = 0.521791 m. Min. coordinate in the x-direction = 0 m, y-direction = -7.07107 m, z-direction = -0.400127 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.3540e+00| -0.397349| 1.978876| 1.645486| 5.093547| 1.917484| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.3522e+00| -0.252045| 2.234760| 1.970250| 5.252026| 2.558863| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.3485e+00| -0.196042| 2.339633| 2.224120| 5.301659| 3.948869| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.3403e+00| -0.220076| 2.386540| 2.365409| 5.264943| 5.948479| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.3394e+00| -0.253573| 2.408600| 2.430554| 5.223815| 7.864579| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.3338e+00| -0.270783| 2.418936| 2.458803| 5.218653| 9.389224| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.3319e+00| -0.286712| 2.403031| 2.476999| 5.213229| 10.603736| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.3288e+00| -0.315381| 2.351751| 2.489815| 5.182543| 11.481006| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.3302e+00| -0.352500| 2.274582| 2.487389| 5.133384| 11.951691| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.3364e+00| -0.405104| 2.187417| 2.462671| 5.069866| 12.022914| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.405104| < -8| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_su2AFLRTest.dat | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |CSV file |surface_flow_su2AFLRTest.csv | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview |flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). |Paraview surface |surface_flow_su2AFLRTest.vtu | Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.883374 Cd = 0.073474 real 1m5.699s user 1m0.255s sys 0m4.463s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_Morph_PyTest.py passed (as expected) ================================================= delaundo: /Users/jenkins/util/delaundo/delaundo/src/delaundo ================================================= + echo 'su2_and_Delaundo_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt su2_and_Delaundo_PyTest.py test; + python -u su2_and_Delaundo_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/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 Reading delaundo mesh file - delaundo_CAPS.mesh Swapping y and z coordinates! Writing Tecplot file .... Tecplot expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing Tecplot file Writing SU2 file .... SU2 expects 2D meshes in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Warning: No boundary condition specified for capsGroup 2DSlice! Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "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: ../delaundo/delaundo_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_su2_CAPS.dat. Surface file name: surface_flow_su2_CAPS. Volume file name: flow_su2_CAPS. Restart file name: restart_flow_su2_CAPS.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Inlet boundary| BC_4| +-----------------------------------------------------------------------+ | Outlet boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Two dimensional problem. 6320 grid points. 12346 volume elements. 5 surface markers. 24 boundary elements in index 0 (Marker = BC_2). 24 boundary elements in index 1 (Marker = BC_3). 24 boundary elements in index 2 (Marker = BC_2). 24 boundary elements in index 3 (Marker = BC_4). 198 boundary elements in index 4 (Marker = BC_5). 12346 triangles. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. There has been a re-orientation of 294 LINE surface elements. Identifying edges and vertices. Setting the control volume structure. Area of the computational grid: 999.917. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 1792.95. Mean K: 10.8142. Standard deviation K: 104.33. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 45.3524| 89.3051| | CV Face Area Aspect Ratio| 1.0235| 15.7138| | CV Sub-Volume Ratio| 1| 7.93643| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 6320| 1/1.00| 10| | 1| 1790| 1/3.53| 7.98287| | 2| 504| 1/3.55| 6.35388| +-------------------------------------------+ Finding max control volume width. Wetted area = 2.07206 m. Area projection in the x-plane = 0.179342 m, y-plane = 1.00053 m. Max. coordinate in the x-direction = 1 m, y-direction = 0.138492 m. Min. coordinate in the x-direction = -0.00104578 m, y-direction = -0.0151891 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_5 is NOT a single straight. Boundary marker BC_2 is a single straight. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 216054| 1| m^2/s^2| 216054| | Velocity-X| 136.119| 1| m/s| 136.119| | Velocity-Y| 0| 1| m/s| 0| | Velocity Magnitude| 136.119| 1| m/s| 136.119| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.4| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 5.6942e-02| -1.163171| 1.073770| 1.341444| 4.312165| 0.062120| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.6284e-02| -1.561828| 0.808636| 0.967487| 3.922716| 0.139775| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.6824e-02| -1.601698| 0.943793| 1.009036| 3.876382| 0.373708| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 5.6950e-02| -1.659374| 1.008221| 1.015635| 3.799753| 0.952935| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 5.7015e-02| -1.663585| 1.011627| 0.956487| 3.788246| 2.344781| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 5.7161e-02| -1.633451| 0.991734| 0.872954| 3.829708| 6.259549| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 5.7063e-02| -1.626398| 0.990123| 0.847075| 3.843511| 26.349556| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 5.6927e-02| -1.643439| 1.009125| 0.895796| 3.825758| -56.104876| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 5.6766e-02| -1.659565| 1.020774| 0.939260| 3.804303| -24.431167| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 5.6781e-02| -1.676757| 1.012633| 0.938320| 3.783310| -21.456835| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.67676| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_su2_CAPS.dat | Writing the forces breakdown file (forces_breakdown_su2_CAPS.dat). |CSV file |surface_flow_su2_CAPS.csv | Writing the forces breakdown file (forces_breakdown_su2_CAPS.dat). |Tecplot binary |flow_su2_CAPS.szplt | Writing the forces breakdown file (forces_breakdown_su2_CAPS.dat). |Tecplot binary surface |surface_flow_su2_CAPS.szplt | Error in tecFileWriterClose: Not all node map values for zone 1 have been written. Currently need 492 more values.0: Error finishing Tecplot file output. Writing the forces breakdown file (forces_breakdown_su2_CAPS.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.805231 Cd = -0.037528 Cmz = 0.414714 Cx = -0.037528 Cy = 0.805231 Pressure Contribution Cl_p = 0.805231 Cd_p = -0.037528 Cmz_p = 0.414714 Cx_p = -0.037528 Cy_p = 0.805231 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 real 0m2.929s user 0m1.876s sys 0m1.030s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_Delaundo_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_and_Tetgen_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt su2_and_Tetgen_PyTest.py test; + python -u su2_and_Tetgen_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/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 = 265 Number of elements = 526 Number of triangle elements = 526 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3137 Total number of elements = 6262 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 - 3137, elements - 6262 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.051426 Creating surface mesh ... Surface mesh seconds: 0.010668 Recovering boundaries... Boundary recovery seconds: 0.10095 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.013094 Suppressing Steiner points ... Steiner suppression seconds: 3.3e-05 Recovering Delaunayness... Delaunay recovery seconds: 0.012265 Refining mesh... 4186 insertions, added 2132 points, 130189 tetrahedra in queue. 1393 insertions, added 396 points, 133609 tetrahedra in queue. 1857 insertions, added 413 points, 131356 tetrahedra in queue. 2476 insertions, added 454 points, 112928 tetrahedra in queue. 3300 insertions, added 466 points, 67068 tetrahedra in queue. 4399 insertions, added 435 points, 292 tetrahedra in queue. 5864 insertions, added 590 points, 479 tetrahedra in queue. Refinement seconds: 1.07457 Smoothing vertices... Mesh smoothing seconds: 0.60688 Improving mesh... Mesh improvement seconds: 0.028427 Jettisoning redundant points. Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.004818 Total running seconds: 1.90391 Statistics: Input points: 3137 Input facets: 6262 Input segments: 9393 Input holes: 2 Input regions: 0 Mesh points: 8091 Mesh tetrahedra: 39789 Mesh faces: 82710 Mesh faces on exterior boundary: 6264 Mesh faces on input facets: 6264 Mesh edges on input segments: 9394 Steiner points on input segments: 1 Steiner points inside domain: 4953 Done meshing using TetGen! Volume mesher did not preserve surface elements - data transfer will NOT be possible. Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "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: ../myMesh/tetgen_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_SU2_Tetgen.dat. Surface file name: surface_flow_pyCAPS_SU2_Tetgen. Volume file name: flow_pyCAPS_SU2_Tetgen. Restart file name: restart_flow_pyCAPS_SU2_Tetgen.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| | | BC_2| +-----------------------------------------------------------------------+ | Far-field| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 8091 grid points. 39789 volume elements. 3 surface markers. 4468 boundary elements in index 0 (Marker = BC_1). 1270 boundary elements in index 1 (Marker = BC_2). 526 boundary elements in index 2 (Marker = BC_3). 39789 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: 2.08926e+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: 30.5804. Standard deviation K: 37.5377. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 1.66644| 84.3027| | CV Face Area Aspect Ratio| 1.51408| 6441.7| | CV Sub-Volume Ratio| 1.03202| 58553.9| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 8091| 1/1.00| 10| | 1| 1351| 1/5.99| 8.25992| | 2| 223| 1/6.06| 6.79647| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.90569 m. Wetted area = 120.046 m^2. Area projection in the x-plane = 10.7914 m^2, y-plane = 4.58502 m^2, z-plane = 57.287 m^2. Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.557773 m. Min. coordinate in the x-direction = -0.00409054 m, y-direction = -7.90569 m, z-direction = -0.41192 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Boundary marker BC_2 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 226952| 1| m^2/s^2| 226952| | Velocity-X| 200.779| 1| m/s| 200.779| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 3.50461| 1| m/s| 3.50461| | Velocity Magnitude| 200.809| 1| m/s| 200.809| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5901| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.8261e-01| 0.617984| 3.049944| 2.093190| 6.108879| 1.810742| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.7935e-01| 0.748911| 3.251769| 2.987153| 6.248586| 2.155825| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.7657e-01| 0.688623| 3.311837| 3.249508| 6.186781| 3.173369| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.7353e-01| 0.587426| 3.265724| 3.310895| 6.060983| 4.532123| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.7275e-01| 0.563655| 3.196458| 3.256149| 6.028232| 5.638253| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 0.563655| < -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 = 0.751804 Cd = 0.13334 Cmx = -0.004647 Cmy = -0.210652 Cmz = 0.001238 Cx = 0.120199 Cy = 0.000192 Cz = 0.754017 real 0m32.139s user 0m30.583s sys 0m1.371s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_Tetgen_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_X43a_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt su2_X43a_PyTest.py test; + python -u su2_X43a_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/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 = 5654 Number of elements = 11304 Number of triangle elements = 11304 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 9462 Total number of elements = 18920 Writing Tecplot file .... Finished writing Tecplot file Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = x43A, index = 1 Name = Farfield, index = 2 Number of surface: nodes - 9462, elements - 18920 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.17478 Creating surface mesh ... Surface mesh seconds: 0.036868 Recovering boundaries... Warning: 6 segments are not recovered. Boundary recovery seconds: 0.263141 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.022884 Suppressing Steiner points ... Steiner suppression seconds: 2.7e-05 Recovering Delaunayness... Delaunay recovery seconds: 0.032856 Refining mesh... 12618 insertions, added 5274 points, 8959 tetrahedra in queue. Refinement seconds: 0.987318 Smoothing vertices... Mesh smoothing seconds: 0.782879 Improving mesh... Mesh improvement seconds: 0.047038 Jettisoning redundant points. Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.011091 Total running seconds: 2.36634 Statistics: Input points: 9462 Input facets: 18920 Input segments: 28380 Input holes: 1 Input regions: 0 Mesh points: 14879 Mesh tetrahedra: 61475 Mesh faces: 132413 Mesh faces on exterior boundary: 18926 Mesh faces on input facets: 18926 Mesh edges on input segments: 28383 Steiner points on input segments: 3 Steiner points inside domain: 5414 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 - x43A Done getting CFD boundary conditions Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 1 Done boundary flags Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" 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: ../myMesh/tetgen_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_x43a_Test.dat. Surface file name: surface_flow_x43a_Test. Volume file name: flow_x43a_Test. Restart file name: restart_flow_x43a_Test.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | 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. 14879 grid points. 61475 volume elements. 2 surface markers. 7622 boundary elements in index 0 (Marker = BC_1). 11304 boundary elements in index 1 (Marker = BC_2). 61475 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 2.67744e+08. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 95.6599. Mean K: 0.525129. Standard deviation K: 2.57985. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 1.97178| 85.1584| | CV Face Area Aspect Ratio| 1.89387| 2232.84| | CV Sub-Volume Ratio| 1| 662807| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 14879| 1/1.00| 10| | 1| 2664| 1/5.59| 8.45431| | 2| 482| 1/5.53| 7.17255| +-------------------------------------------+ Finding max control volume width. Semi-span length = 30 m. Wetted area = 13596.7 m^2. Area projection in the x-plane = 761.676 m^2, y-plane = 2062.48 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| 3.2579e-01| 2.730957| 5.664998| 4.728682| 8.730433| -0.398804| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.1002e-01| 3.137446| 6.177776| 5.665282| 9.126833| -0.137986| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.0747e-01| 3.221739| 6.293564| 5.717532| 9.173826| -0.037061| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.0336e-01| 3.189146| 6.230574| 5.640455| 9.149183| -0.012053| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.9969e-01| 3.223156| 6.256981| 5.536034| 9.185450| -0.028725| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 3.22316| < -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: 85 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 = -3.497481 Cd = 121.75903 Cmx = -17.512377 Cmy = 9356.955958 Cmz = 278.947628 Cx = 121.775208 Cy = 2.435697 Cz = 2.879687 real 0m13.962s user 0m17.058s sys 0m2.234s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_X43a_PyTest.py passed (as expected) ================================================= ./execute_PyTestRegression.sh: line 413: ulimit: stack size: cannot modify limit: Operation not permitted flowCart: /Users/jenkins/util/cart3d/cart3d_v1.5.9_OSX64_ICC--22.11.16/bin/OSX64_ICC//flowCart ================================================= + echo 'cart3d_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt cart3d_PyTest.py test; + python -u cart3d_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt Loading AIM Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.796888 Tessellating body 1 with MaxEdge = 0.094922 Sag = 0.003797 Angle = 15.000000 Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 9 > autoInputs.out Executing: ./aero.csh > aero.out C_A 0.023693377 C_Y -0.0012129281 C_N 0.065395002 C_D 0.025961197 C_S -0.0012129281 C_L 0.064528278 C_l 0.0510971 C_m 0.000248187 C_n -0.017525 C_M_x 0.0504544 C_M_y 0.000248187 C_M_z -0.0192976 real 0m19.107s user 0m31.322s sys 0m1.546s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case cart3d_PyTest.py passed (as expected) ================================================= ================================================= + echo 'cart3d_OpenMDAO_3_alpha_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt cart3d_OpenMDAO_3_alpha_PyTest.py test; + python -u cart3d_OpenMDAO_3_alpha_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt ---------------------------------------- >>> alpha [2.] 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 - alpha Done getting CFD design variables Getting CFD functional....... Number of design variables - 1 Objective name - CL2 Done getting CFD functional Body size = 3.625615 Tessellating body 1 with MaxEdge = 0.090640 Sag = 0.003626 Angle = 15.000000 Executing: autoInputs -r 30.000000 -nDiv 5 -maxR 7 -mesh2d > autoInputs.out o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:49:53) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1 (01:49:55) aero.csh done o case M0.5901A2B0_DP1, averaging data over 1 cycle(s) >>> CL2 [0.01631562] CL 0.12773309 ---------------------------------------- ---------------------------------------- >>> alpha [2.] >>> CL2 [0.01631562] CL 0.12773309 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:49:58) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1 (01:50:01) 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 (01:50:02) Linearizing cut-cells (01:50:02) ... done o Number of simultaneous xsensit jobs: 1 (01:50:02) Computing gradients (01:50:06) ... done o case M0.5901A2B0_DP1, averaging data over 1 cycle(s) >>> CL2_alpha [[0.01572627]] ======================================== 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= 1.63156D-02 |proj g|= 1.57263D-02 ---------------------------------------- >>> alpha [1.98427373] o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:50:08) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1 (01:50:11) aero.csh done o case M0.5901A1.98427B0_DP1, averaging data over 1 cycle(s) >>> CL2 [0.01606724] CL 0.12675617 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:50:13) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1 (01:50:16) 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 (01:50:16) Linearizing cut-cells (01:50:16) ... done o Number of simultaneous xsensit jobs: 1 (01:50:16) Computing gradients (01:50:20) ... done o case M0.5901A1.98427B0_DP1, averaging data over 1 cycle(s) >>> CL2_alpha [[0.01560329]] ======================================== At iterate 1 f= 1.60672D-02 |proj g|= 1.56033D-02 ---------------------------------------- >>> alpha [-0.01099175] o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:50:23) Running aero.csh on 2 core(s) in M0.5901A-0.0109918B0_DP1 (01:50:26) aero.csh done o case M0.5901A-0.0109918B0_DP1, averaging data over 1 cycle(s) >>> CL2 [6.05653687e-06] CL 0.00246101 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:50:28) Running aero.csh on 2 core(s) in M0.5901A-0.0109918B0_DP1 (01:50:31) 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 (01:50:32) Linearizing cut-cells (01:50:32) ... done o Number of simultaneous xsensit jobs: 1 (01:50:32) Computing gradients (01:50:36) ... done o case M0.5901A-0.0109918B0_DP1, averaging data over 1 cycle(s) >>> CL2_alpha [[0.00031042]] ======================================== At iterate 2 f= 6.05654D-06 |proj g|= 3.10424D-04 ---------------------------------------- >>> alpha [-0.05149286] o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:50:38) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1 (01:50:41) aero.csh done o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s) >>> CL2 [2.59817201e-10] CL 1.612e-05 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:50:43) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1 (01:50:46) 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 (01:50:46) Linearizing cut-cells (01:50:46) ... done o Number of simultaneous xsensit jobs: 1 (01:50:46) Computing gradients (01:50:50) ... done o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s) >>> CL2_alpha [[2.03612486e-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 (01:50:53) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1 (01:50:55) aero.csh done o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s) >>> CL2 [9.26120217e-15] CL 1e-07 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:50:57) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1 (01:51:00) 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 (01:51:00) Linearizing cut-cells (01:51:00) ... done o Number of simultaneous xsensit jobs: 1 (01:51:00) Computing gradients (01:51:04) ... done o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s) >>> CL2_alpha [[1.21394333e-08]] ======================================== At iterate 4 f= 9.26120D-15 |proj g|= 1.21394D-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 9.261D-15 F = 9.2612021713000013E-015 CONVERGENCE: NORM_OF_PROJECTED_GRADIENT_<=_PGTOL Optimization Complete ----------------------------------- Optimized value: [-0.05176027] real 1m24.227s user 0m55.921s sys 0m15.882s + 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_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/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_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/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 (01:51:12) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:51:26) 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 (01:51:32) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:51:53) 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 (01:51:54) Linearizing cut-cells (01:51:56) ... done o Number of simultaneous xsensit jobs: 1 (01:51:56) Computing gradients (01:52:00) ... 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 (01:52:05) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:52:21) 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 (01:52:27) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:52:49) 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 (01:52:50) Linearizing cut-cells (01:52:52) ... done o Number of simultaneous xsensit jobs: 1 (01:52:52) Computing gradients (01:52:56) ... 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 [-6.4716878] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.635635 Tessellating body 1 with MaxEdge = 0.018178 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 (01:53:01) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:53:17) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [0.00980712] CL -0.0990178 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:53:23) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:53:46) aero.csh done Max memory allowed: 32 GB Flow hexes: 37091 Estimated cutter memory: 0.003709 GB / DV Estimated xsensit memory: 0.070473 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (01:53:47) Linearizing cut-cells (01:53:49) ... done o Number of simultaneous xsensit jobs: 1 (01:53:49) Computing gradients (01:53:53) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[-0.00318447]] ======================================== ---------------------------------------- >>> twist [-0.15773817] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.625777 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 (01:53:59) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:54:15) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [2.57283248e-07] CL -0.00057627 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:54:21) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:54:45) 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 (01:54:46) Linearizing cut-cells (01:54:48) ... done o Number of simultaneous xsensit jobs: 1 (01:54:48) Computing gradients (01:54:52) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[-1.67854875e-05]] ======================================== At iterate 2 f= 2.57283D-07 |proj g|= 1.67855D-05 ---------------------------------------- >>> twist [-0.12478737] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.625742 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 (01:54:57) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:55:13) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [1.7930502e-08] CL 0.00016606 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (01:55:20) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (01:55:44) 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 (01:55:44) Linearizing cut-cells (01:55:46) ... done o Number of simultaneous xsensit jobs: 1 (01:55:46) Computing gradients (01:55:50) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[4.43472903e-06]] ======================================== At iterate 3 f= 1.79305D-08 |proj g|= 4.43473D-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 4.435D-06 1.793D-08 F = 1.7930502041000001E-008 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- Optimized values: [-0.12478737] real 4m45.887s user 6m45.403s sys 0m27.193s + 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_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt fun3d_Morph_PyTest.py test; + python -u fun3d_Morph_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64/ESP/DARWIN64/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 x86_64 AFLR2 : Compile Date 04/23/24 @ 11:49AM 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 x86_64 AFLR4 : Compile Date 04/23/24 @ 11:49AM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.7.0 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 EGADS : OpenCASCADE Version 7.7.0 EGADS : --------------------------------------- Volume mesh: Number of nodes = 79623 Number of elements = 464233 Number of triangles = 15680 Number of quadrilatarals = 0 Number of tetrahedrals = 448553 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 0m15.012s user 0m12.299s sys 0m1.385s + 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! ================================================= ================================================= [GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64') [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_MemcheckCaps/7.7/CAPS/CFD/DARWIN64') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/CFD/DARWIN64') [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_MemcheckCaps/7.7/CAPS/CFD/DARWIN64') [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_MemcheckCaps/7.7/CAPS/CFD/DARWIN64') [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_MemcheckCaps/7.7/CAPS/CFD/DARWIN64') [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_MemcheckCaps/CASREV=7.7,ESPTEST=CAPS/CFD,ESP_ARCH=DARWIN64,buildnode=macys #1383'. [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