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Skipping 439 KB.. Full LogGetting surface mesh for body 3 (of 3) Body 1 (of 3) Number of nodes = 9607 Number of elements = 19210 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 19210 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 6142 Number of elements = 12280 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 12280 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 265 Number of elements = 526 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 526 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 16014 Total number of elements = 32016 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 - 16014, elements - 32016 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.378392 Creating surface mesh ... Surface mesh seconds: 0.058805 Recovering boundaries... Boundary recovery seconds: 0.196861 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.072544 Recovering Delaunayness... Delaunay recovery seconds: 0.112414 Refining mesh... 21346 insertions, added 17000 points, 773281 tetrahedra in queue. 7108 insertions, added 2714 points, 325605 tetrahedra in queue. Refinement seconds: 3.04154 Smoothing vertices... Mesh smoothing seconds: 4.27865 Improving mesh... Mesh improvement seconds: 0.150213 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.023162 Total running seconds: 8.3142 Statistics: Input points: 16014 Input facets: 32016 Input segments: 48024 Input holes: 2 Input regions: 0 Mesh points: 37066 Mesh tetrahedra: 178778 Mesh faces: 373564 Mesh faces on exterior boundary: 32016 Mesh faces on input facets: 32016 Mesh edges on input segments: 48024 Steiner points inside domain: 21052 Done meshing using TetGen! Getting CFD boundary conditions Boundary condition name - Wing1 Boundary condition name - Wing2 Boundary condition name - Farfield Done getting CFD boundary conditions Python library was linked, but will not be used! Writing MAPBC file .... Finished writing MAPBC file Warning: The fun3d.nml file will be overwritten! Writing fun3d.nml Info: No recognized data transfer names found. NOT Running fun3d! real 0m17.279s user 0m17.913s sys 0m0.270s + status=0 + set +x ============================================= CAPS verification (using c-executables) case ./fun3dTetgenTest passed (as expected) ============================================= All tests pass! ================================================= ================================================= ++ '[' '!' -z '-L/Users/jenkins/util/ESP/Python/ESP_Python-3.9.13/lib -lpython3.9 -ldl -framework CoreFoundation' ']' ++ ./execute_PyTestRegression.sh CFD ================================================= Using python : /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/bin/python ================================================= Running.... CFD PyTests ================================================= + echo 'su2_and_AFLR2_NodeDist_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt su2_and_AFLR2_NodeDist_PyTest.py test; + python -u su2_and_AFLR2_NodeDist_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.14.6 AFLR2 : Version Date 11/20/22 @ 09:21PM AFLR2 : Compile OS Darwin 22.3.0 arm64 AFLR2 : Compile Date 03/08/23 @ 05:04PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 224 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 224 224 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 46 94 AFLR2 IG : Nodes, Faces = 92 186 AFLR2 IG : Nodes, Faces = 138 278 AFLR2 IG : Nodes, Faces = 184 370 AFLR2 IG : Nodes, Faces = 196 394 AFLR2 IG : Nodes, Faces = 224 450 AFLR2 IG : Nodes, Faces = 228 450 AFLR2 IG : Nodes, Faces = 224 224 AFLR2 : CPU Time = 0.000 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GG : Nodes, Faces = 224 224 AFLR2 GG : Nodes, Faces = 440 656 AFLR2 GG : Nodes, Faces = 649 1074 AFLR2 GG : Nodes, Faces = 853 1482 AFLR2 GG : Nodes, Faces = 1050 1876 AFLR2 GG : Nodes, Faces = 1238 2252 AFLR2 GG : Nodes, Faces = 1421 2618 AFLR2 GG : Nodes, Faces = 1594 2964 AFLR2 GG : Nodes, Faces = 1760 3296 AFLR2 GG : Nodes, Faces = 1915 3606 AFLR2 GG : Nodes, Faces = 2063 3902 AFLR2 GG : Nodes, Faces = 2202 4180 AFLR2 GG : Nodes, Faces = 2314 4404 AFLR2 GG : Nodes, Faces = 2423 4622 AFLR2 GG : Nodes, Faces = 2528 4832 AFLR2 GG : Nodes, Faces = 2634 5044 AFLR2 GG : Nodes, Faces = 2732 5240 AFLR2 GG : Nodes, Faces = 2831 5438 AFLR2 GG : Nodes, Faces = 2927 5630 AFLR2 GG : Nodes, Faces = 3018 5812 AFLR2 GG : Nodes, Faces = 3109 5994 AFLR2 GG : Nodes, Faces = 3202 6180 AFLR2 GG : Nodes, Faces = 3295 6366 AFLR2 GG : Nodes, Faces = 3386 6548 AFLR2 GG : Nodes, Faces = 3464 6704 AFLR2 GG : Nodes, Faces = 3535 6846 AFLR2 GG : Nodes, Faces = 3594 6964 AFLR2 GG : Nodes, Faces = 3639 7054 AFLR2 GG : Nodes, Faces = 3671 7118 AFLR2 GG : Nodes, Faces = 3691 7158 AFLR2 GG : Nodes, Faces = 3705 7186 AFLR2 GG : Nodes, Faces = 3712 7200 AFLR2 GG : Nodes, Faces = 3715 7206 AFLR2 : CPU Time = 0.004 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 3715 7206 AFLR2 : CPU Time = 0.000 seconds AFLR2 : DONE Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 3715 Number of elements = 7430 Number of tris = 7206 Number of quad = 0 Writing SU2 file .... SU2 expects 2D meshes be in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.4.0) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.4.0 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2022, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.4. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_5. Surface(s) plotted in the output file: BC_5, BC_2. Input mesh file name: ../aflr2/aflr2.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_SU2_aflr2.dat. Surface file name: surface_flow_pyCAPS_SU2_aflr2. Volume file name: flow_pyCAPS_SU2_aflr2. Restart file name: restart_flow_pyCAPS_SU2_aflr2.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Inlet boundary| BC_4| +-----------------------------------------------------------------------+ | Outlet boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Two dimensional problem. 3715 grid points. 7206 volume elements. 4 surface markers. 98 boundary elements in index 0 (Marker = BC_2). 24 boundary elements in index 1 (Marker = BC_3). 24 boundary elements in index 2 (Marker = BC_4). 78 boundary elements in index 3 (Marker = BC_5). 7206 triangles. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 7206 TRIANGLE volume elements. There has been a re-orientation of 73 LINE surface elements. Identifying edges and vertices. Setting the control volume structure. Area of the computational grid: 999.917. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 177.06. Mean K: 1.97232. Standard deviation K: 13.0434. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 63.4343| 90| | CV Face Area Aspect Ratio| 1| 5.23543| | CV Sub-Volume Ratio| 1| 3.11804| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 3715| 1/1.00| 10| | 1| 1048| 1/3.54| 7.96696| | 2| 298| 1/3.52| 6.37252| +-------------------------------------------+ Finding max control volume width. Wetted area = 2.06136 m. Area projection in the x-plane = 0.178383 m, y-plane = 0.994925 m. Max. coordinate in the x-direction = 1 m, y-direction = 0.138389 m. Min. coordinate in the x-direction = -0.000250564 m, y-direction = -0.0152 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_5 is NOT a single straight. Boundary marker BC_2 is NOT a single straight. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 216054| 1| m^2/s^2| 216054| | Velocity-X| 136.119| 1| m/s| 136.119| | Velocity-Y| 0| 1| m/s| 0| | Velocity Magnitude| 136.119| 1| m/s| 136.119| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.4| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver +----------------------------------------------------------------------------------------------------------------------------------------------+ | 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| 3.1481e-02| -0.385358| 2.453598| 1.625650| 5.369499| 0.360138| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.3257e-02| -0.512634| 2.087781| 1.374671| 4.973554| 1.183037| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.3561e-02| -0.792582| 1.733529| 1.142729| 4.657622| 3.896326| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.2017e-02| -0.880738| 1.486539| 1.023158| 4.334759| 14.592305| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.0605e-02| -0.987528| 1.351478| 0.932491| 4.191092| 111.166908| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 3.3122e-02| -1.104038| 1.188715| 0.874765| 3.951824| -483.950418| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 3.3259e-02| -1.178622| 1.124587| 0.844310| 3.820426| 127.328901| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 3.4240e-02| -1.243517| 1.097463| 0.824871| 3.768858| 40.162063| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 3.5981e-02| -1.287932| 1.075843| 0.810640| 3.733440| 25.154599| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 3.5579e-02| -1.300689| 1.046363| 0.775886| 3.684244| 21.097842| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.30069| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_pyCAPS_SU2_aflr2.dat | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). |CSV file |surface_flow_pyCAPS_SU2_aflr2.csv | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). |Tecplot binary |flow_pyCAPS_SU2_aflr2.szplt | Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). |Tecplot binary surface |surface_flow_pyCAPS_SU2_aflr2.szplt| Error in tecFileWriterClose: Not all node map values for zone 1 have been written. Currently need 352 more values.0: Error finishing Tecplot file output. Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.650457 Cd = 0.030831 Cmz = 0.373226 Cx = 0.030831 Cy = 0.650457 Pressure Contribution Cl_p = 0.650457 Cd_p = 0.030831 Cmz_p = 0.373226 Cx_p = 0.030831 Cy_p = 0.650457 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 real 0m2.466s user 0m1.655s sys 0m0.357s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_AFLR2_NodeDist_PyTest.py passed (as expected) ================================================= ================================================= + echo 'su2_and_AFLR2_PyTest.py test;' + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt su2_and_AFLR2_PyTest.py test; + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt + python -u su2_and_AFLR2_PyTest.py -outLevel=0 Saving geometry Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 5 Name = 2DSlice, index = 1 Name = TunnelWall, index = 2 Name = OutFlow, index = 3 Name = InFlow, index = 4 Name = Airfoil, index = 5 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = TunnelWall, index = 1 Name = OutFlow, index = 2 Name = InFlow, index = 3 Name = Airfoil, index = 4 Getting mesh sizing parameters Mesh sizing name - 2DSlice Mesh sizing name - Airfoil Mesh sizing name - InFlow Mesh sizing name - OutFlow Mesh sizing name - TunnelWall Done getting mesh sizing parameters Getting 2D mesh for body 1 (of 1) AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.14.6 AFLR2 : Version Date 11/20/22 @ 09:21PM AFLR2 : Compile OS Darwin 22.3.0 arm64 AFLR2 : Compile Date 03/08/23 @ 05:04PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR2 IC : INPUT DATA CHECK AFLR2 IC : Nodes, Faces = 545 0 AFLR2 : CPU Time = 0.000 seconds AFLR2 EG : EDGE GRID RE-GENERATION AFLR2 EG : Nodes, Edges = 545 545 AFLR2 : CPU Time = 0.000 seconds AFLR2 IG : INITIAL GRID GENERATION AFLR2 IG : Nodes, Faces = 0 2 AFLR2 IG : Nodes, Faces = 110 222 AFLR2 IG : Nodes, Faces = 220 442 AFLR2 IG : Nodes, Faces = 330 662 AFLR2 IG : Nodes, Faces = 440 882 AFLR2 IG : Nodes, Faces = 517 1036 AFLR2 IG : Nodes, Faces = 545 1092 AFLR2 IG : Nodes, Faces = 549 1092 AFLR2 IG : Nodes, Faces = 545 545 AFLR2 : CPU Time = 0.001 seconds AFLR2 GG : FIELD GRID GENERATION AFLR2 GGp: Nodes, Faces = 545 545 AFLR2 GGp: Nodes, Faces = 1083 1621 AFLR2 GGp: Nodes, Faces = 1616 2687 AFLR2 GGp: Nodes, Faces = 2144 3743 AFLR2 GGp: Nodes, Faces = 2661 4777 AFLR2 GGp: Nodes, Faces = 3171 5797 AFLR2 GGp: Nodes, Faces = 3672 6799 AFLR2 GGp: Nodes, Faces = 4158 7771 AFLR2 GGp: Nodes, Faces = 4653 8761 AFLR2 GGp: Nodes, Faces = 5142 9739 AFLR2 GGp: Nodes, Faces = 5608 10671 AFLR2 GGp: Nodes, Faces = 6055 11565 AFLR2 GGp: Nodes, Faces = 6482 12419 AFLR2 GGp: Nodes, Faces = 6880 13215 AFLR2 GGp: Nodes, Faces = 7257 13969 AFLR2 GGp: Nodes, Faces = 7614 14683 AFLR2 GGp: Nodes, Faces = 7947 15349 AFLR2 GGp: Nodes, Faces = 8276 16007 AFLR2 GGp: Nodes, Faces = 8575 16605 AFLR2 GGp: Nodes, Faces = 8869 17193 AFLR2 GGp: Nodes, Faces = 9140 17735 AFLR2 GGp: Nodes, Faces = 9401 18257 AFLR2 GGp: Nodes, Faces = 9654 18763 AFLR2 GGp: Nodes, Faces = 9887 19229 AFLR2 GGp: Nodes, Faces = 10110 19675 AFLR2 GGp: Nodes, Faces = 10315 20085 AFLR2 GGp: Nodes, Faces = 10497 20449 AFLR2 GGp: Nodes, Faces = 10656 20767 AFLR2 GGp: Nodes, Faces = 10791 21037 AFLR2 GGp: Nodes, Faces = 10919 21293 AFLR2 GGp: Nodes, Faces = 11022 21499 AFLR2 GGp: Nodes, Faces = 11092 21639 AFLR2 GGp: Nodes, Faces = 11145 21745 AFLR2 GGp: Nodes, Faces = 11156 21767 AFLR2 : CPU Time = 0.039 seconds AFLR2 QI : QUALITY IMPROVEMENT AFLR2 QI : Nodes, Faces = 11156 21767 AFLR2 QI : Nodes, Faces = 11155 819 AFLR2 QI : Nodes, Faces = 11155 10473 AFLR2 QI : Nodes, Faces = 11155 21765 AFLR2 QI : Nodes, Faces = 11154 811 AFLR2 QI : Nodes, Faces = 11154 10476 AFLR2 QI : Nodes, Faces = 11154 21763 AFLR2 QI : Nodes, Faces = 11154 805 AFLR2 QI : Nodes, Faces = 11154 10479 AFLR2 QI : Nodes, Faces = 11154 21763 AFLR2 QI : Nodes, Faces = 11154 911 AFLR2 QI : Nodes, Faces = 11154 10426 AFLR2 QI : Nodes, Faces = 11154 21763 AFLR2 QI : Nodes, Faces = 11153 915 AFLR2 QI : Nodes, Faces = 11153 10423 AFLR2 QI : Nodes, Faces = 11153 917 AFLR2 QI : Nodes, Faces = 11153 10423 AFLR2 : CPU Time = 0.025 seconds AFLR2 : DONE EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)! EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)! EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)! Writing AFLR3 file .... Finished writing AFLR3 file Number of nodes = 11153 Number of elements = 11885 Number of tris = 917 Number of quad = 10423 Writing TECPLOT file: pyCAPS_su2_aflr2.dat .... Finished writing TECPLOT file Writing SU2 file .... SU2 expects 2D meshes be in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.4.0) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.4.0 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2022, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.4. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_5. Surface(s) plotted in the output file: BC_5, BC_2. Input mesh file name: ../aflr2/aflr2.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_pyCAPS_su2_aflr2.dat. Surface file name: surface_flow_pyCAPS_su2_aflr2. Volume file name: flow_pyCAPS_su2_aflr2. Restart file name: restart_flow_pyCAPS_su2_aflr2.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_5| | | BC_2| +-----------------------------------------------------------------------+ | Inlet boundary| BC_4| +-----------------------------------------------------------------------+ | Outlet boundary| BC_3| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Two dimensional problem. 11153 grid points. 11340 volume elements. 4 surface markers. 98 boundary elements in index 0 (Marker = BC_2). 24 boundary elements in index 1 (Marker = BC_3). 24 boundary elements in index 2 (Marker = BC_4). 399 boundary elements in index 3 (Marker = BC_5). 917 triangles. 10423 quadrilaterals. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 917 TRIANGLE volume elements. There has been a re-orientation of 10423 QUADRILATERAL volume elements. There has been a re-orientation of 73 LINE surface elements. Identifying edges and vertices. Setting the control volume structure. Area of the computational grid: 999.878. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 385.665. Mean K: 2.15881. Standard deviation K: 17.7215. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 49.3184| 90| | CV Face Area Aspect Ratio| 1.00035| 33.4982| | CV Sub-Volume Ratio| 1.00001| 7.89914| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11153| 1/1.00| 10| | 1| 2702| 1/4.13| 7.38309| | 2| 549| 1/4.92| 4.99198| +-------------------------------------------+ Finding max control volume width. Wetted area = 2.06265 m. Area projection in the x-plane = 0.211192 m, y-plane = 0.997011 m. Max. coordinate in the x-direction = 1 m, y-direction = 0.102037 m. Min. coordinate in the x-direction = 0.000323229 m, y-direction = -0.108492 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_5 is NOT a single straight. Boundary marker BC_2 is NOT a single straight. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 216054| 1| m^2/s^2| 216054| | Velocity-X| 136.119| 1| m/s| 136.119| | Velocity-Y| 0| 1| m/s| 0| | Velocity Magnitude| 136.119| 1| m/s| 136.119| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.4| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver +----------------------------------------------------------------------------------------------------------------------------------------------+ | 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| 9.5414e-02| 0.071067| 2.739763| 1.616077| 5.599701| 0.055267| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 9.1723e-02| -0.447576| 2.193837| 1.571349| 5.070382| 0.046028| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.0002e-01| -0.561159| 2.074597| 1.490746| 4.953698| 0.033910| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.0304e-01| -0.723326| 1.921155| 1.390756| 4.790278| 0.049695| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.0747e-01| -0.876572| 1.825653| 1.275093| 4.637161| 0.133976| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.0882e-01| -1.029177| 1.759196| 1.156078| 4.482282| 0.368542| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.0834e-01| -1.215334| 1.704909| 1.114966| 4.286060| 0.974759| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.0981e-01| -1.329970| 1.644937| 1.145030| 4.116982| 2.716332| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.0991e-01| -1.270672| 1.570739| 1.155400| 4.139480| 16.569216| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.0897e-01| -1.221243| 1.499646| 1.130319| 4.189559| -6.277653| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.22124| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_pyCAPS_su2_aflr2.dat | Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). |CSV file |surface_flow_pyCAPS_su2_aflr2.csv | Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). |Tecplot binary |flow_pyCAPS_su2_aflr2.szplt | Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). |Tecplot binary surface |surface_flow_pyCAPS_su2_aflr2.szplt| Error in tecFileWriterClose: Not all node map values for zone 1 have been written. Currently need 994 more values.0: Error finishing Tecplot file output. Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ 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 0m3.208s user 0m2.908s sys 0m0.358s + 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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value Writing TECPLOT file: AFLR4_Mesh.dat .... 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 9.14.6 AFLR2 : Version Date 11/20/22 @ 09:21PM AFLR2 : Compile OS Darwin 22.3.0 arm64 AFLR2 : Compile Date 03/08/23 @ 05:04PM 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 11.3.17 AFLR4 : Version Date 03/03/23 @ 03:12PM AFLR4 : Compile OS Darwin 22.3.0 arm64 AFLR4 : Compile Date 03/08/23 @ 05:05PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.23 EGADS : OpenCASCADE Version 7.4.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.23 EGADS : OpenCASCADE Version 7.4.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 40106 Number of elements = 231493 Number of triangles = 12446 Number of quadrilatarals = 0 Number of tetrahedrals = 219047 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing TECPLOT file: AFLR3_Mesh.dat .... 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 "BlackBird (7.4.0) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.4.0 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2022, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.5901. 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_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 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. 40106 grid points. 219047 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). 219047 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: 61.8668. Standard deviation K: 266.942. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 19.4002| 84.2743| | CV Face Area Aspect Ratio| 1.11297| 22794.1| | CV Sub-Volume Ratio| 1.03791| 323406| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 40106| 1/1.00| 10| | 1| 6579| 1/6.1| 8.21123| | 2| 1031| 1/6.38| 6.64047| +-------------------------------------------+ Finding max control volume width. Semi-span length = 7.90569 m. Wetted area = 118.035 m^2. Area projection in the x-plane = 11.1422 m^2, y-plane = 4.96703 m^2, z-plane = 55.4177 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 +----------------------------------------------------------------------------------------------------------------------------------------------+ | 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| 1.1956e+00| -0.068917| 2.293323| 2.029016| 5.421978| 1.969146| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.1807e+00| -0.039315| 2.438299| 2.155039| 5.458848| 2.667937| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.1892e+00| 0.007948| 2.550133| 2.398011| 5.504215| 4.074496| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.1978e+00| -0.030652| 2.599575| 2.535779| 5.459451| 6.009099| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.1964e+00| -0.079846| 2.606644| 2.589425| 5.407223| 7.708472| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.1891e+00| -0.091591| 2.594064| 2.603542| 5.403677| 8.911754| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.1907e+00| -0.100566| 2.554136| 2.607537| 5.395466| 9.751694| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.1965e+00| -0.131653| 2.491918| 2.604156| 5.355684| 10.227571| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.1986e+00| -0.179635| 2.431915| 2.587606| 5.295934| 10.320451| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.1993e+00| -0.220634| 2.402874| 2.546473| 5.253378| 10.117312| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.220634| < -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). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.795115 Cd = 0.07859 Cmx = -0.000197 Cmy = -0.202378 Cmz = -0.000267 Cx = 0.064701 Cy = -0.000139 Cz = 0.796365 Pressure Contribution Cl_p = 0.795115 Cd_p = 0.07859 Cmx_p = -0.000197 Cmy_p = -0.202378 Cmz_p = -0.000267 Cx_p = 0.064701 Cy_p = -0.000139 Cz_p = 0.796365 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 0m36.055s user 0m27.797s sys 0m0.759s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_and_AFLR4_AFLR3_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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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 be 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 - delaundoMesh.mesh Swapping y and z coordinates! Writing TECPLOT file: delaundoMesh.dat .... Finished writing TECPLOT file Writing SU2 file .... SU2 expects 2D meshes be in the x-y plane... attempting to rotate mesh! Swapping z and y coordinates! Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Airfoil Boundary condition name - InFlow Boundary condition name - OutFlow Boundary condition name - TunnelWall Warning: No boundary condition specified for capsGroup 2DSlice! Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.4.0) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.4.0 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2022, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.4. 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/delaundoMesh.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_delaundoMesh.dat. Surface file name: surface_flow_delaundoMesh. Volume file name: flow_delaundoMesh. Restart file name: restart_flow_delaundoMesh.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. 6335 grid points. 12376 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). 12376 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: 10.8141. 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| 89.2457| | CV Face Area Aspect Ratio| 1.03245| 15.7098| | CV Sub-Volume Ratio| 1| 7.93642| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 6335| 1/1.00| 10| | 1| 1815| 1/3.49| 8.0289| | 2| 519| 1/3.5| 6.4401| +-------------------------------------------+ 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 = -0.00104577 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 +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 4.9924e-02| -1.163686| 1.073255| 1.340929| 4.311650| 0.061671| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.2636e-02| -1.568377| 0.814909| 0.963677| 3.916705| 0.144353| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.0387e-02| -1.613815| 0.940123| 1.014538| 3.865902| 0.383098| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 5.0021e-02| -1.678204| 0.986567| 1.029402| 3.782002| 0.970161| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 5.0735e-02| -1.673240| 0.982512| 0.972025| 3.776795| 2.379908| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 5.3476e-02| -1.632262| 0.968047| 0.868654| 3.827903| 6.320909| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 5.4557e-02| -1.626018| 0.975724| 0.835054| 3.842259| 25.935722| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 5.4955e-02| -1.650839| 1.000183| 0.890573| 3.818757| -60.978870| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 5.6409e-02| -1.679741| 1.014343| 0.938142| 3.785304| -25.297357| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 5.6805e-02| -1.692890| 1.005186| 0.937842| 3.767062| -21.973132| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.69289| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_delaundoMesh.dat | Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat). |CSV file |surface_flow_delaundoMesh.csv | Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat). |Tecplot binary |flow_delaundoMesh.szplt | Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat). |Tecplot binary surface |surface_flow_delaundoMesh.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_delaundoMesh.dat). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.798939 Cd = -0.03636 Cmz = 0.411603 Cx = -0.03636 Cy = 0.798939 Pressure Contribution Cl_p = 0.798939 Cd_p = -0.03636 Cmz_p = 0.411603 Cx_p = -0.03636 Cy_p = 0.798939 Viscous Contribution Cl_v = 0.0 Cd_v = 0.0 Cmz_v = 0.0 Cx_v = 0.0 Cy_v = 0.0 real 0m2.326s user 0m1.814s sys 0m0.418s + 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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt su2_and_Tetgen_PyTest.py test; + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt + python -u su2_and_Tetgen_PyTest.py -outLevel=0 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 node elements = 0 Number of line elements = 0 Number of triangle elements = 4468 Number of quadrilateral elements = 0 Body 2 (of 3) Number of nodes = 636 Number of elements = 1268 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 1268 Number of quadrilateral elements = 0 Body 3 (of 3) Number of nodes = 265 Number of elements = 526 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 526 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3137 Total number of elements = 6262 Writing TECPLOT file: egadsTessMesh_Surf_0.dat .... Finished writing TECPLOT file Writing TECPLOT file: egadsTessMesh_Surf_1.dat .... Finished writing TECPLOT file Writing TECPLOT file: egadsTessMesh_Surf_2.dat .... 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: 0.058726 Creating surface mesh ... Surface mesh seconds: 0.007131 Recovering boundaries... Boundary recovery seconds: 0.152927 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.013831 Suppressing Steiner points ... Steiner suppression seconds: 8e-06 Recovering Delaunayness... Delaunay recovery seconds: 0.019379 Refining mesh... 4186 insertions, added 2159 points, 126369 tetrahedra in queue. 1393 insertions, added 415 points, 129993 tetrahedra in queue. 1857 insertions, added 443 points, 128610 tetrahedra in queue. 2476 insertions, added 560 points, 116391 tetrahedra in queue. 3300 insertions, added 523 points, 73871 tetrahedra in queue. 4399 insertions, added 397 points, 746 tetrahedra in queue. Refinement seconds: 1.10137 Smoothing vertices... Mesh smoothing seconds: 0.892294 Improving mesh... Mesh improvement seconds: 0.042168 Jettisoning redundant points. Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.006924 Total running seconds: 2.29506 Statistics: Input points: 3137 Input facets: 6262 Input segments: 9393 Input holes: 2 Input regions: 0 Mesh points: 8158 Mesh tetrahedra: 40383 Mesh faces: 83898 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: 5020 Done meshing using TetGen! Volume mesher did not preserve surface elements - data transfer will NOT be possible. Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing1 Boundary condition name - Wing2 Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.4.0) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.4.0 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2022, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.5901. 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_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 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. 8158 grid points. 40383 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). 40383 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.)| 1.92303| 83.9055| | CV Face Area Aspect Ratio| 1.55295| 3521.13| | CV Sub-Volume Ratio| 1.01617| 206050| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 8158| 1/1.00| 10| | 1| 1352| 1/6.03| 8.23927| | 2| 218| 1/6.2| 6.72677| +-------------------------------------------+ 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 +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 2.1198e-01| 0.616193| 3.048153| 2.091399| 6.107088| 1.805051| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.1391e-01| 0.775229| 3.247319| 3.001437| 6.275319| 2.174893| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.0271e-01| 0.702974| 3.288113| 3.247932| 6.198943| 3.210083| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 2.0189e-01| 0.601014| 3.220958| 3.293492| 6.064222| 4.596839| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.0788e-01| 0.593648| 3.197132| 3.233731| 6.058200| 5.787584| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 0.593648| < -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). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = 0.759974 Cd = 0.131311 Cmx = -0.003194 Cmy = -0.212257 Cmz = 0.000553 Cx = 0.118028 Cy = 0.000335 Cz = 0.76215 real 0m9.317s user 0m7.090s sys 0m0.389s + 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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt su2_X43a_PyTest.py test; + python -u su2_X43a_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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 = 3817 Number of elements = 7634 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 7634 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 5654 Number of elements = 11304 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 11304 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 9471 Total number of elements = 18938 Writing TECPLOT file: egadsTessMesh_Surf_0.dat .... Finished writing TECPLOT file Writing TECPLOT file: egadsTessMesh_Surf_1.dat .... 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 - 9471, elements - 18938 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 0.160525 Creating surface mesh ... Surface mesh seconds: 0.046514 Recovering boundaries... Warning: 4 segments are not recovered. Boundary recovery seconds: 0.426958 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.033662 Suppressing Steiner points ... Steiner suppression seconds: 2e-05 Recovering Delaunayness... Delaunay recovery seconds: 0.069756 Refining mesh... 12628 insertions, added 5171 points, 10497 tetrahedra in queue. Refinement seconds: 1.50815 Smoothing vertices... Mesh smoothing seconds: 1.2586 Improving mesh... Mesh improvement seconds: 0.067069 Jettisoning redundant points. Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.007925 Total running seconds: 3.58978 Statistics: Input points: 9471 Input facets: 18938 Input segments: 28407 Input holes: 1 Input regions: 0 Mesh points: 14824 Mesh tetrahedra: 61034 Mesh faces: 131539 Mesh faces on exterior boundary: 18942 Mesh faces on input facets: 18942 Mesh edges on input segments: 28409 Steiner points on input segments: 2 Steiner points inside domain: 5351 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 Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.4.0) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.4.0 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2022, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 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_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 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. 14824 grid points. 61034 volume elements. 2 surface markers. 7638 boundary elements in index 0 (Marker = BC_1). 11304 boundary elements in index 1 (Marker = BC_2). 61034 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: 0.525659. Standard deviation K: 2.58024. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.041314| 83.9178| | CV Face Area Aspect Ratio| 1.62826| 13202.4| | CV Sub-Volume Ratio| 1| 1.24042e+07| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 14824| 1/1.00| 10| | 1| 2668| 1/5.56| 8.46899| | 2| 492| 1/5.42| 7.23073| +-------------------------------------------+ Finding max control volume width. Semi-span length = 30 m. Wetted area = 13597 m^2. Area projection in the x-plane = 761.658 m^2, y-plane = 2062.86 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 +----------------------------------------------------------------------------------------------------------------------------------------------+ | 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| 3.9849e-01| 2.731645| 5.665596| 4.729423| 8.731121| -0.374100| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.9487e-01| 3.120118| 6.139645| 5.659982| 9.120238| -0.138499| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.9750e-01| 3.198604| 6.246170| 5.767210| 9.165358| -0.054805| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.8608e-01| 3.243196| 6.288748| 5.704421| 9.196215| -0.048476| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.7517e-01| 3.234245| 6.291775| 5.521178| 9.205466| -0.072036| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 3.23424| < -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 131 non-physical points in the solution. Warning: 63 reconstructed states for upwinding are non-physical. ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Total Force - Pressure + Viscous Cl = -8.581041 Cd = 119.121674 Cmx = -19.065106 Cmy = 9458.970655 Cmz = 200.291547 Cx = 119.407518 Cy = 2.431409 Cz = -2.334934 real 0m17.314s user 0m23.475s sys 0m0.656s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case su2_X43a_PyTest.py passed (as expected) ================================================= ./execute_PyTestRegression.sh: line 404: 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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt cart3d_PyTest.py test; + python -u cart3d_PyTest.py -outLevel=0 + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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 0.050108722 C_Y -0.0015626888 C_N 0.0065057682 C_D 0.050305245 C_S -0.0015626888 C_L 0.0047530359 C_l 0.00381162 C_m -0.00346146 C_n -0.0401149 C_M_x 0.00240931 C_M_y -0.00346146 C_M_z -0.0402235 real 0m47.966s user 0m40.503s sys 0m1.678s + 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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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 (10:42:05) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1 (10:42:15) 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 (10:42:16) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1 (10:42:23) 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 (10:42:23) Linearizing cut-cells (10:42:23) ... done o Number of simultaneous xsensit jobs: 1 (10:42:23) Computing gradients (10:42:27) ... 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 (10:42:29) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1 (10:42:34) 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 (10:42:35) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1 (10:42:53) 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 (10:42:53) Linearizing cut-cells (10:42:53) ... done o Number of simultaneous xsensit jobs: 1 (10:42:53) Computing gradients (10:42:57) ... 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 (10:42:58) Running aero.csh on 2 core(s) in M0.5901A-0.0109917B0_DP1 (10:43:02) aero.csh done o case M0.5901A-0.0109917B0_DP1, averaging data over 1 cycle(s) >>> CL2 [6.05653711e-06] CL 0.00246101 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (10:43:03) Running aero.csh on 2 core(s) in M0.5901A-0.0109917B0_DP1 (10:43:07) 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 (10:43:08) Linearizing cut-cells (10:43:08) ... done o Number of simultaneous xsensit jobs: 1 (10:43:08) Computing gradients (10:43:12) ... done o case M0.5901A-0.0109917B0_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 (10:43:13) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1 (10:43:27) aero.csh done o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s) >>> CL2 [2.59817062e-10] CL 1.612e-05 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (10:43:28) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1 (10:43:32) 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 (10:43:33) Linearizing cut-cells (10:43:33) ... done o Number of simultaneous xsensit jobs: 1 (10:43:33) Computing gradients (10:43:37) ... done o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s) >>> CL2_alpha [[2.03612433e-06]] ======================================== At iterate 3 f= 2.59817D-10 |proj g|= 2.03612D-06 ---------------------------------------- >>> alpha [-0.05176027] o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (10:43:38) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1 (10:43:45) aero.csh done o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s) >>> CL2 [9.25766089e-15] CL 1e-07 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (10:43:46) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1 (10:43:50) 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 (10:43:50) Linearizing cut-cells (10:43:50) ... done o Number of simultaneous xsensit jobs: 1 (10:43:51) Computing gradients (10:43:55) ... done o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s) >>> CL2_alpha [[1.21372408e-08]] ======================================== At iterate 4 f= 9.25766D-15 |proj g|= 1.21372D-08 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 1 4 5 4 0 0 1.214D-08 9.258D-15 F = 9.2576608860000000E-015 CONVERGENCE: NORM_OF_PROJECTED_GRADIENT_<=_PGTOL Optimization Complete ----------------------------------- Optimized value: [-0.05176027] real 1m58.309s user 1m8.020s sys 0m11.343s + 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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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 (10:44:00) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:44:30) 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 (10:44:32) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:45:17) 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 (10:45:17) Linearizing cut-cells (10:45:19) ... done o Number of simultaneous xsensit jobs: 1 (10:45:19) Computing gradients (10:45:23) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[0.00209614]] ======================================== 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|= 2.09614D-03 ---------------------------------------- >>> twist [3.99790386] 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 (10:45:28) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:46:08) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [0.00411103] CL 0.0641104 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (10:46:10) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:46:37) 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 (10:46:37) Linearizing cut-cells (10:46:39) ... done o Number of simultaneous xsensit jobs: 1 (10:46:39) Computing gradients (10:46:43) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[0.00209539]] ======================================== At iterate 1 f= 4.11103D-03 |proj g|= 2.09539D-03 ---------------------------------------- >>> twist [-1.80569534] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.627699 Tessellating body 1 with MaxEdge = 0.018138 Sag = 0.000907 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 (10:46:47) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:47:23) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [0.00077483] CL -0.027831 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (10:47:26) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:47:56) aero.csh done Max memory allowed: 32 GB Flow hexes: 37739 Estimated cutter memory: 0.003774 GB / DV Estimated xsensit memory: 0.071704 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (10:47:56) Linearizing cut-cells (10:47:58) ... done o Number of simultaneous xsensit jobs: 1 (10:47:58) Computing gradients (10:48:02) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[-0.00093593]] ======================================== At iterate 2 f= 7.74827D-04 |proj g|= 9.35931D-04 ---------------------------------------- >>> twist [-0.01381239] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.625629 Tessellating body 1 with MaxEdge = 0.018128 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 (10:48:06) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:48:27) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [1.42535052e-06] CL 0.00122587 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (10:48:29) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:49:06) aero.csh done Max memory allowed: 32 GB Flow hexes: 38636 Estimated cutter memory: 0.003864 GB / DV Estimated xsensit memory: 0.073408 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (10:49:06) Linearizing cut-cells (10:49:09) ... done o Number of simultaneous xsensit jobs: 1 (10:49:09) Computing gradients (10:49:13) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[3.9839431e-05]] ======================================== At iterate 3 f= 1.42535D-06 |proj g|= 3.98394D-05 ---------------------------------------- >>> twist [-0.08697266] Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = Wing, index = 1 Body size = 3.625704 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 (10:49:17) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:49:46) aero.csh done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2 [8.44871607e-07] CL 0.00093859 ---------------------------------------- ======================================== o Evaluating Cart3D functionals and/or gradients ATTENTION: using static geometry ../inputs/Components.i.tri (10:49:49) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1 (10:50:30) aero.csh done Max memory allowed: 32 GB Flow hexes: 37754 Estimated cutter memory: 0.003775 GB / DV Estimated xsensit memory: 0.071733 GB / DV Available threads: 2 # DVs: 1 o Number of simultaneous cutter jobs: 1 (10:50:30) Linearizing cut-cells (10:50:32) ... done o Number of simultaneous xsensit jobs: 1 (10:50:32) Computing gradients (10:50:36) ... done o case M0.5901A0B0_DP1, averaging data over 1 cycle(s) >>> CL2_twist [[3.04136986e-05]] ======================================== At iterate 4 f= 8.44872D-07 |proj g|= 3.04137D-05 * * * 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 3.041D-05 8.449D-07 F = 8.4487160666999986E-007 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- Optimized values: [-0.08697266] real 6m41.966s user 6m29.223s sys 0m16.616s + 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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt fun3d_Morph_PyTest.py test; + python -u fun3d_Morph_PyTest.py -outLevel=0 -noAnalysis + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/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: pyCAPS_AFLR4_AFLR3.dat .... 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 9.14.6 AFLR2 : Version Date 11/20/22 @ 09:21PM AFLR2 : Compile OS Darwin 22.3.0 arm64 AFLR2 : Compile Date 03/08/23 @ 05:04PM 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 11.3.17 AFLR4 : Version Date 03/03/23 @ 03:12PM AFLR4 : Compile OS Darwin 22.3.0 arm64 AFLR4 : Compile Date 03/08/23 @ 05:05PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.23 EGADS : OpenCASCADE Version 7.4.1 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.23 EGADS : OpenCASCADE Version 7.4.1 EGADS : --------------------------------------- Volume mesh: Number of nodes = 82911 Number of elements = 483743 Number of triangles = 15694 Number of quadrilatarals = 0 Number of tetrahedrals = 468049 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing TECPLOT file: pyCAPS_AFLR4_AFLR3_VolMesh.dat .... 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 0m13.743s user 0m10.685s sys 0m0.445s + 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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1') [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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1') [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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1') [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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1') [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_UndefinedCaps/7.4/CAPS/CFD/DARWINM1') [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Reference build recorder is not configured [Static Analysis] Obtaining reference build from same job (7.4,CAPS/CFD,DARWINM1,viggen) [Static Analysis] Using reference build 'ESP_UndefinedCaps/CASREV=7.4,ESPTEST=CAPS/CFD,ESP_ARCH=DARWINM1,buildnode=viggen #176' to compute new, fixed, and outstanding issues [Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0 [Static Analysis] Evaluating quality gates [Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1 [Static Analysis] -> All quality gates have been passed [Static Analysis] Health report is disabled - skipping [Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues) [Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_UndefinedCaps/CASREV=7.4,ESPTEST=CAPS/CFD,ESP_ARCH=DARWINM1,buildnode=viggen #178'. [Checks API] No suitable checks publisher found. [PostBuildScript] - [INFO] Executing post build scripts. [PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX [WS-CLEANUP] Deleting project workspace... [WS-CLEANUP] done Finished: SUCCESS