The Jenkins Controller is preparing for shutdown. No new builds can be started.
Skipping 716 KB.. Full LogMapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 12 Number of elements = 12 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 4 Elemental Quad4 = 8 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Temperature_SM.csv Number of variables = 16 Number of data points = 361 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Temperature' Rank 0: src = 2.097780e+01, tgt = 2.097780e+01, diff = 9.379164e-13 Extracting external thermal loads from data transfer.... TransferName = Skin_Top Number of Nodes = 9 (total = 9) Extracting external thermal loads from data transfer.... TransferName = Skin_Bottom Number of Nodes = 9 (total = 18) Extracting external thermal loads from data transfer.... TransferName = Skin_Tip Number of Nodes = 4 (total = 16) Writing Nastran grid and connectivity file (in free field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing TACS instruction file.... Writing analysis cards Writing load ADD cards Writing constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Running PostAnalysis ...... tacs real 0m28.463s user 0m23.116s sys 0m2.319s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelasticSimple_Temperature_SU2_and_TACS.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Did not run examples for: Mystran ================================================= All tests pass! ================================================= ================================================= ++ cd /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/CAPS/legacy/examples/regressionTest ++ ./execute_PyTestRegression.sh AEROELASTIC ================================================= Legacy Using python : /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/ESP/venv/bin/python ================================================= Running.... AEROELASTIC PyTests ================================================= + rm -rf aeroelasticSimple_Pressure_SU2_and_Astros + echo 'aeroelasticSimple_Pressure_SU2_and_Astros.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt aeroelasticSimple_Pressure_SU2_and_Astros.py test; + python -u aeroelasticSimple_Pressure_SU2_and_Astros.py -verbosity=0 -workDir=runDirectory -noPlotData + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Running PreAnalysis ...... tetgen Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Running PostAnalysis ...... tetgen Body 1 (of 1) Number of nodes = 12449 Number of elements = 24894 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 24894 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 12449 Total number of elements = 24894 Running PreAnalysis ...... tetgen Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Number of surface: nodes - 12449, elements - 24894 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Running PostAnalysis ...... tetgen Running PreAnalysis ...... su2 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Skin Boundary condition name - SymmPlane Done getting CFD boundary conditions Info: No recognized data transfer names found. Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../runDirectory_AeroelasticSimple_Pressure_tetgen_tetgenAIM/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| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Pressure_SA.dat. Surface file name: surface_flow_aeroelasticSimple_Pressure_SA. Volume file name: flow_aeroelasticSimple_Pressure_SA. Restart file name: restart_flow_aeroelasticSimple_Pressure_SA.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 22559 grid points. 98644 volume elements. 3 surface markers. 342 boundary elements in index 0 (Marker = BC_1). 12856 boundary elements in index 1 (Marker = BC_2). 11696 boundary elements in index 2 (Marker = BC_3). 98644 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 63999.5. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 1594.52. Mean K: 49.8216. Standard deviation K: 81.7526. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 12.7569| 83.9993| | CV Face Area Aspect Ratio| 1.80581| 23185.6| | CV Sub-Volume Ratio| 1| 77755.6| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 22559| 1/1.00| 10| | 1| 4207| 1/5.36| 8.56989| | 2| 987| 1/4.26| 7.92833| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 10.0438 m^2. Area projection in the x-plane = 0.679139 m^2, y-plane = 0.327414 m^2, z-plane = 4.84583 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380458 m. Min. coordinate in the x-direction = -0.000478065 m, y-direction = -2.86151e-18 m, z-direction = -0.0467319 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 7.1547e-01| -1.523015| 0.609935| 0.080731| 3.946091| -0.730159| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 6.6675e-01| -1.304187| 1.158339| 0.940576| 4.166256| -0.217956| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 6.6082e-01| -1.429691| 1.178606| 1.010958| 4.033394| 2.094727| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 6.3011e-01| -1.367153| 1.041900| 0.919423| 4.096463| -17.368218| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 6.0234e-01| -1.451051| 0.942431| 0.855378| 4.011094| -8.664140| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.45105| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Pressure_SA.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SA.dat). |CSV file |surface_flow_aeroelasticSimple_Pressure_SA.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SA.dat). |Tecplot binary |flow_aeroelasticSimple_Pressure_SA.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SA.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Pressure_SA.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Pressure_SA.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Executing dataTransfer ...... No variable name provided - defaulting to variable - Pressure Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 180 Number of elements = 194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 32 Elemental Quad4 = 162 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Rib_Root Property name - Skin Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureAero No "groupName" specified for Load tuple pressureAero, going to use load name Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SA.csv Number of variables = 16 Number of data points = 5887 No variable name provided - defaulting to variable - Pressure Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SA.csv Number of variables = 16 Number of data points = 5887 No variable name provided - defaulting to variable - Pressure Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Pressure_SA.csv Number of variables = 16 Number of data points = 5887 Running PreAnalysis ...... astros Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 81 (total = 81) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 81 (total = 162) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 16 (total = 178) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Running Astros...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Running PostAnalysis ...... astros WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.aimName' is deprecated. Please use 'name'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisInfo' is deprecated. Please use 'Analysis.info'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsBound.fillVertexSets' is deprecated. Please use 'None'! WARNING: 'capsAnalysis.getAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsBound.executeTransfer' is deprecated. Please use 'None'! WARNING: 'capsBound.getDestData' is deprecated. Please use 'vertexSet["name"].dataSet["variableName"].getData'! WARNING: 'DataSet.getData' is deprecated. Please use 'DataSet.data'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 0m18.474s user 0m15.809s sys 0m1.827s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case aeroelasticSimple_Pressure_SU2_and_Astros.py passed (as expected) ================================================= ================================================= + rm -rf aeroelasticSimple_Displacement_SU2_and_Astros + echo 'aeroelasticSimple_Displacement_SU2_and_Astros.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt aeroelasticSimple_Displacement_SU2_and_Astros.py test; + python -u aeroelasticSimple_Displacement_SU2_and_Astros.py -verbosity=0 -workDir=runDirectory -noPlotData + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Running PreAnalysis ...... tetgen Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Running PostAnalysis ...... tetgen Body 1 (of 1) Number of nodes = 12449 Number of elements = 24894 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 24894 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 12449 Total number of elements = 24894 Running PreAnalysis ...... tetgen Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Number of surface: nodes - 12449, elements - 24894 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000QT1.00e-16A Done meshing using TetGen! Running PostAnalysis ...... tetgen Running PreAnalysis ...... astros Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 180 Number of elements = 194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 32 Elemental Quad4 = 162 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Rib_Root Property name - Skin Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureInternal Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Running Astros...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Running PostAnalysis ...... astros Executing dataTransfer ...... No variable name provided - defaulting to variable - Displacement Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Skin Boundary condition name - SymmPlane Done getting CFD boundary conditions No variable name provided - defaulting to variable - Displacement No variable name provided - defaulting to variable - Displacement Running PreAnalysis ...... su2 Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticSimple_Displacement_SA_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../runDirectory_AeroelasticSimple_Displacement_tetgen_tetgenAIM/tetgen_0.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../runDirectory_AeroelasticSimple_Displacement_tetgen_tetgenAIM/tetgen_0.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 22559 grid points. 98644 volume elements. 3 surface markers. 342 boundary elements in index 0 (Marker = BC_1). 12856 boundary elements in index 1 (Marker = BC_2). 11696 boundary elements in index 2 (Marker = BC_3). 98644 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 2.644481 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../runDirectory_AeroelasticSimple_Displacement_tetgen_tetgenAIM/tetgen_0.su2| |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../runDirectory_AeroelasticSimple_Displacement_tetgen_tetgenAIM/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| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Displacement_SA.dat. Surface file name: surface_flow_aeroelasticSimple_Displacement_SA. Volume file name: flow_aeroelasticSimple_Displacement_SA. Restart file name: restart_flow_aeroelasticSimple_Displacement_SA.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 22559 grid points. 98644 volume elements. 3 surface markers. 342 boundary elements in index 0 (Marker = BC_1). 12856 boundary elements in index 1 (Marker = BC_2). 11696 boundary elements in index 2 (Marker = BC_3). 98644 tetrahedra. 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 4164 TETRAHEDRON volume elements. There has been a re-orientation of 721 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 63997.7. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 1963.01. Mean K: 62.1337. Standard deviation K: 144.97. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 4.10523| 83.0894| | CV Face Area Aspect Ratio| 1.79967| 21772.3| | CV Sub-Volume Ratio| 1.00009| 1.15114e+07| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 22559| 1/1.00| 10| | 1| 4216| 1/5.35| 8.576| | 2| 994| 1/4.24| 7.94703| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.89957 m. Wetted area = 12.4772 m^2. Area projection in the x-plane = 3.08369 m^2, y-plane = 1.33891 m^2, z-plane = 4.78464 m^2. Max. coordinate in the x-direction = 2.53729 m, y-direction = 3.89957 m, z-direction = 0.526515 m. Min. coordinate in the x-direction = -0.00039489 m, y-direction = -2.86151e-18 m, z-direction = -0.706932 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 8.1120e-01| -0.781959| 1.689594| 1.305458| 4.687147| 0.026467| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 8.4825e-01| -0.460038| 2.013474| 1.780488| 5.017361| -0.000510| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 8.6214e-01| -0.646472| 2.043898| 1.872141| 4.822937| 0.009300| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 8.6784e-01| -0.706944| 1.989522| 1.799633| 4.759822| 0.025851| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 8.7281e-01| -0.672257| 1.916984| 1.673304| 4.795683| 0.046289| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.672257| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Displacement_SA.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SA.dat). |CSV file |surface_flow_aeroelasticSimple_Displacement_SA.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SA.dat). |Tecplot binary |flow_aeroelasticSimple_Displacement_SA.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SA.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Displacement_SA.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Displacement_SA.dat). +-----------------------------------------------------------------------+ Warning: there are 356 non-physical points in the solution. Warning: 149 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.aimName' is deprecated. Please use 'name'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisInfo' is deprecated. Please use 'Analysis.info'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsBound.fillVertexSets' is deprecated. Please use 'None'! WARNING: 'capsBound.executeTransfer' is deprecated. Please use 'None'! WARNING: 'capsBound.getDestData' is deprecated. Please use 'vertexSet["name"].dataSet["variableName"].getData'! WARNING: 'DataSet.getData' is deprecated. Please use 'DataSet.data'! WARNING: 'capsAnalysis.getAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 0m35.450s user 0m21.914s sys 0m3.020s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case aeroelasticSimple_Displacement_SU2_and_Astros.py passed (as expected) ================================================= ================================================= + rm -rf aeroelasticSimple_Iterative_SU2_and_Astros + echo 'aeroelasticSimple_Iterative_SU2_and_Astros.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt aeroelasticSimple_Iterative_SU2_and_Astros.py test; + python -u aeroelasticSimple_Iterative_SU2_and_Astros.py -verbosity=0 -workDir=runDirectory + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Running PreAnalysis ...... egads Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Running PostAnalysis ...... egads Body 1 (of 1) Number of nodes = 12449 Number of elements = 24894 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 24894 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 12449 Total number of elements = 24894 Running PreAnalysis ...... tetgen Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Number of surface: nodes - 12449, elements - 24894 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 1.13607 Creating surface mesh ... Surface mesh seconds: 0.035473 Recovering boundaries... Boundary recovery seconds: 0.137457 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.037732 Recovering Delaunayness... Delaunay recovery seconds: 0.040108 Refining mesh... 16594 insertions, added 9193 points, 319384 tetrahedra in queue. 5525 insertions, added 626 points, 65154 tetrahedra in queue. 7365 insertions, added 240 points, 1338 tetrahedra in queue. Refinement seconds: 2.24305 Smoothing vertices... Mesh smoothing seconds: 1.29912 Improving mesh... Mesh improvement seconds: 0.035735 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.011035 Total running seconds: 4.97629 Statistics: Input points: 12449 Input facets: 24894 Input segments: 37341 Input holes: 0 Input regions: 0 Mesh points: 22559 Mesh tetrahedra: 98644 Mesh faces: 209735 Mesh faces on exterior boundary: 24894 Mesh faces on input facets: 24894 Mesh edges on input segments: 37341 Steiner points inside domain: 10110 Done meshing using TetGen! Running PostAnalysis ...... tetgen Executing dataTransfer "Displacement"...... Running PreAnalysis ...... su2 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Skin Boundary condition name - SymmPlane Done getting CFD boundary conditions Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticSimple_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../runDirectory_AeroelasticSimple_Iterative_SA_tetgen_tetgenAIM/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| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative.dat. Surface file name: surface_flow_aeroelasticSimple_Iterative. Volume file name: flow_aeroelasticSimple_Iterative. Restart file name: restart_flow_aeroelasticSimple_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 22559 grid points. 98644 volume elements. 3 surface markers. 342 boundary elements in index 0 (Marker = BC_1). 12856 boundary elements in index 1 (Marker = BC_2). 11696 boundary elements in index 2 (Marker = BC_3). 98644 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 63999.5. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 1594.52. Mean K: 49.8216. Standard deviation K: 81.7526. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 12.7569| 83.9993| | CV Face Area Aspect Ratio| 1.80581| 23185.6| | CV Sub-Volume Ratio| 1| 77755.6| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 22559| 1/1.00| 10| | 1| 4207| 1/5.36| 8.56989| | 2| 987| 1/4.26| 7.92833| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 10.0438 m^2. Area projection in the x-plane = 0.679139 m^2, y-plane = 0.327414 m^2, z-plane = 4.84583 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380458 m. Min. coordinate in the x-direction = -0.000478065 m, y-direction = -2.86151e-18 m, z-direction = -0.0467319 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 8.0039e-01| -1.523015| 0.609935| 0.080731| 3.946091| -0.730159| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 7.8445e-01| -1.304187| 1.158339| 0.940576| 4.166256| -0.217956| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 7.9082e-01| -1.429691| 1.178606| 1.010958| 4.033394| 2.094727| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 7.9327e-01| -1.367153| 1.041900| 0.919423| 4.096463| -17.368218| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 7.9211e-01| -1.451051| 0.942431| 0.855378| 4.011094| -8.664140| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.45105| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |CSV file |surface_flow_aeroelasticSimple_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary |flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Executing dataTransfer "Pressure"...... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 1 Name = Skin, index = 1 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Skin, index = 1 Name = Rib_Root, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 180 Number of elements = 194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 32 Elemental Quad4 = 162 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 1 Material name - Madeupium Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - Rib_Root Property name - Skin Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureAero No "groupName" specified for Load tuple pressureAero, going to use load name Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 5887 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 5887 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 5887 Running PreAnalysis ...... astros Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 81 (total = 81) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 81 (total = 162) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 16 (total = 178) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Running Astros...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Running PostAnalysis ...... astros Executing dataTransfer "Displacement"...... Running PreAnalysis ...... su2 Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticSimple_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../runDirectory_AeroelasticSimple_Iterative_SA_tetgen_tetgenAIM/tetgen_0.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../runDirectory_AeroelasticSimple_Iterative_SA_tetgen_tetgenAIM/tetgen_0.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 22559 grid points. 98644 volume elements. 3 surface markers. 342 boundary elements in index 0 (Marker = BC_1). 12856 boundary elements in index 1 (Marker = BC_2). 11696 boundary elements in index 2 (Marker = BC_3). 98644 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 2.885625 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../runDirectory_AeroelasticSimple_Iterative_SA_tetgen_tetgenAIM/tetgen_0.su2| |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../runDirectory_AeroelasticSimple_Iterative_SA_tetgen_tetgenAIM/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| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative.dat. Surface file name: surface_flow_aeroelasticSimple_Iterative. Volume file name: flow_aeroelasticSimple_Iterative. Restart file name: restart_flow_aeroelasticSimple_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 22559 grid points. 98644 volume elements. 3 surface markers. 342 boundary elements in index 0 (Marker = BC_1). 12856 boundary elements in index 1 (Marker = BC_2). 11696 boundary elements in index 2 (Marker = BC_3). 98644 tetrahedra. 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 21981 TETRAHEDRON volume elements. There has been a re-orientation of 3560 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 70780.7. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 3476.02. Mean K: 44.3899. Standard deviation K: 174.259. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.294588| 82.35| | CV Face Area Aspect Ratio| 1.59729| 264565| | CV Sub-Volume Ratio| 1.00237| 9.68698e+08| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 22559| 1/1.00| 10| | 1| 4216| 1/5.35| 8.576| | 2| 1006| 1/4.19| 7.97888| +-------------------------------------------+ Finding max control volume width. Semi-span length = 8.64457 m. Wetted area = 422.06 m^2. Area projection in the x-plane = 127.222 m^2, y-plane = 150.625 m^2, z-plane = 17.3669 m^2. Max. coordinate in the x-direction = 3.25205 m, y-direction = 8.64457 m, z-direction = 5.77239 m. Min. coordinate in the x-direction = -0.150417 m, y-direction = -2.86151e-18 m, z-direction = -69.8353 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 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| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 9.0156e-01| 2.497833| 5.464549| 5.493406| 7.966939| -0.147599| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 9.0409e-01| 2.635820| 5.357309| 5.420465| 8.064943| -0.212663| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 8.9529e-01| 2.745159| 5.333528| 5.403812| 8.165941| -0.256643| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 8.8422e-01| 2.848543| 5.362919| 5.427791| 8.162681| -0.188291| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 8.8437e-01| 2.898930| 5.471261| 5.476218| 8.244534| -0.162863| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 2.89893| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticSimple_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |CSV file |surface_flow_aeroelasticSimple_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary |flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelasticSimple_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticSimple_Iterative.dat). +-----------------------------------------------------------------------+ Warning: there are 1125 non-physical points in the solution. Warning: 513 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Executing dataTransfer "Pressure"...... Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 5887 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 5887 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 16 Number of data points = 5887 Running PreAnalysis ...... astros Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 81 (total = 81) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 81 (total = 162) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 16 (total = 178) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Running Astros...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Running PostAnalysis ...... astros WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisInfo' is deprecated. Please use 'Analysis.info'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsBound.fillVertexSets' is deprecated. Please use 'None'! WARNING: 'capsBound.executeTransfer' is deprecated. Please use 'None'! WARNING: 'capsBound.getDestData' is deprecated. Please use 'vertexSet["name"].dataSet["variableName"].getData'! WARNING: 'DataSet.getData' is deprecated. Please use 'DataSet.data'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 0m37.552s user 0m31.840s sys 0m3.843s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_SU2_and_Astros.py passed (as expected) ================================================= ================================================= + rm -rf aeroelastic_Iterative_SU2_and_Astros + echo 'aeroelastic_Iterative_SU2_and_Astros.py test;' + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt aeroelastic_Iterative_SU2_and_Astros.py test; + python -u aeroelastic_Iterative_SU2_and_Astros.py -verbosity=0 -workDir=runDirectory + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt Running PreAnalysis ...... egads Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Getting surface mesh for body 1 (of 1) Running PostAnalysis ...... egads Body 1 (of 1) Number of nodes = 25819 Number of elements = 51634 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 51634 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 25819 Total number of elements = 51634 Running PreAnalysis ...... tetgen Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Number of surface: nodes - 25819, elements - 51634 Getting volume mesh Generating volume mesh using TetGen..... Tetgen input string = pYq1.500/0.000T1.00e-16A Delaunizing vertices... Delaunay seconds: 2.61643 Creating surface mesh ... Surface mesh seconds: 0.074107 Recovering boundaries... Boundary recovery seconds: 0.28398 Removing exterior tetrahedra ... Spreading region attributes. Exterior tets removal seconds: 0.082193 Recovering Delaunayness... Delaunay recovery seconds: 0.070675 Refining mesh... 34416 insertions, added 14656 points, 515068 tetrahedra in queue. 11460 insertions, added 501 points, 93186 tetrahedra in queue. 15276 insertions, added 385 points, 6920 tetrahedra in queue. Refinement seconds: 21.1895 Smoothing vertices... Mesh smoothing seconds: 2.16695 Improving mesh... Mesh improvement seconds: 0.066563 Writing nodes. Writing elements. Writing faces. Writing edges. Output seconds: 0.024346 Total running seconds: 26.5757 Statistics: Input points: 25819 Input facets: 51634 Input segments: 77451 Input holes: 0 Input regions: 0 Mesh points: 41966 Mesh tetrahedra: 173588 Mesh faces: 372993 Mesh faces on exterior boundary: 51634 Mesh faces on input facets: 51634 Mesh edges on input segments: 77451 Steiner points inside domain: 16147 Done meshing using TetGen! Running PostAnalysis ...... tetgen Executing dataTransfer "Displacement"...... Running PreAnalysis ...... su2 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Skin Boundary condition name - SymmPlane Done getting CFD boundary conditions Writing SU2 data transfer files Writing SU2 Motion File - aeroelastic_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../runDirectory_Aeroelastic_Iterative_SA_tetgen_tetgenAIM/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| | 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_aeroelastic_Iterative.dat. Surface file name: surface_flow_aeroelastic_Iterative. Volume file name: flow_aeroelastic_Iterative. Restart file name: restart_flow_aeroelastic_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 41966 grid points. 173588 volume elements. 3 surface markers. 534 boundary elements in index 0 (Marker = BC_1). 31605 boundary elements in index 1 (Marker = BC_2). 19495 boundary elements in index 2 (Marker = BC_3). 173588 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. All volume elements are correctly orientend. All surface elements are correctly orientend. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 63999.5. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 1061.04. Mean K: 24.6984. Standard deviation K: 62.0805. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 6.17732| 85.0593| | CV Face Area Aspect Ratio| 1.67567| 13243.7| | CV Sub-Volume Ratio| 1| 203352| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 41966| 1/1.00| 10| | 1| 7997| 1/5.25| 8.63179| | 2| 1924| 1/4.16| 8.05289| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 10.1964 m^2. Area projection in the x-plane = 0.682432 m^2, y-plane = 0.335222 m^2, z-plane = 4.92026 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380458 m. Min. coordinate in the x-direction = -0.000478065 m, y-direction = -2.86151e-18 m, z-direction = -0.0467319 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 is NOT a single plane. Boundary marker BC_2 is a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.5563e+00| -1.910877| 0.181600| -0.221602| 3.558228| -0.654949| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.5472e+00| -1.276786| 1.056348| 0.859623| 4.197535| -0.247732| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.5554e+00| -1.296162| 1.234750| 1.052145| 4.173195| 1.987333| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.5683e+00| -1.109196| 1.173381| 1.032120| 4.355240| -13.040977| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.5690e+00| -0.796285| 1.368670| 0.988769| 4.677226| -7.874010| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -0.796285| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelastic_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |CSV file |surface_flow_aeroelastic_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary |flow_aeroelastic_Iterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelastic_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Executing dataTransfer "Pressure"...... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 3 Name = Skin_Top, index = 1 Name = Skin_Bottom, index = 2 Name = Skin_Tip, index = 3 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Ribs_and_Spars, index = 1 Name = Skin, index = 2 Name = Rib_Root, index = 3 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 746 Number of elements = 898 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 120 Elemental Quad4 = 778 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 3 Property name - Rib_Root Property name - Ribs_and_Spars Property name - Skin Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - edgeConstraint No "constraintType" specified for Constraint tuple edgeConstraint, defaulting to "ZeroDisplacement" Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 1 Load name - pressureAero No "groupName" specified for Load tuple pressureAero, going to use load name Done getting FEA loads Optimization Control tuple is NULL - Default optimization control is used Getting FEA optimization control....... Done getting FEA Optimization Control Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 9800 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 9800 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 9800 Running PreAnalysis ...... astros Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 330 (total = 330) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 330 (total = 660) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 30 (total = 690) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Running Astros...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Running PostAnalysis ...... astros Executing dataTransfer "Displacement"...... Running PreAnalysis ...... su2 Writing SU2 data transfer files Writing SU2 Motion File - aeroelastic_Iterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../runDirectory_Aeroelastic_Iterative_SA_tetgen_tetgenAIM/tetgen_0.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../runDirectory_Aeroelastic_Iterative_SA_tetgen_tetgenAIM/tetgen_0.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 41966 grid points. 173588 volume elements. 3 surface markers. 534 boundary elements in index 0 (Marker = BC_1). 31605 boundary elements in index 1 (Marker = BC_2). 19495 boundary elements in index 2 (Marker = BC_3). 173588 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 6.746903 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../runDirectory_Aeroelastic_Iterative_SA_tetgen_tetgenAIM/tetgen_0.su2| |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 1 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 1 m. Reference origin for moment evaluation is (0, 0, 0). Surface(s) where the force coefficients are evaluated: BC_3. Surface(s) plotted in the output file: BC_3. Surface(s) affected by the design variables: BC_3. Input mesh file name: ../runDirectory_Aeroelastic_Iterative_SA_tetgen_tetgenAIM/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| | 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_aeroelastic_Iterative.dat. Surface file name: surface_flow_aeroelastic_Iterative. Volume file name: flow_aeroelastic_Iterative. Restart file name: restart_flow_aeroelastic_Iterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_3| +-----------------------------------------------------------------------+ | Far-field| BC_1| +-----------------------------------------------------------------------+ | Symmetry plane| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 41966 grid points. 173588 volume elements. 3 surface markers. 534 boundary elements in index 0 (Marker = BC_1). 31605 boundary elements in index 1 (Marker = BC_2). 19495 boundary elements in index 2 (Marker = BC_3). 173588 tetrahedra. 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 79053 TETRAHEDRON volume elements. There has been a re-orientation of 21812 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 8.35716e+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: 112078. Mean K: 29.9202. Standard deviation K: 1077.84. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.0499425| 87.3832| | CV Face Area Aspect Ratio| 1.74501| 4.71002e+16| | CV Sub-Volume Ratio| 1.00083| 1.81918e+09| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 41966| 1/1.00| 10| | 1| 8002| 1/5.24| 8.63359| | 2| 1944| 1/4.12| 8.0807| +-------------------------------------------+ Finding max control volume width. Semi-span length = 53.5038 m. Wetted area = 19247.6 m^2. Area projection in the x-plane = 6141.41 m^2, y-plane = 6386.67 m^2, z-plane = 371.345 m^2. Max. coordinate in the x-direction = 11.4788 m, y-direction = 53.5038 m, z-direction = 20.7885 m. Min. coordinate in the x-direction = -2.11918 m, y-direction = -0.798855 m, z-direction = -697.391 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_3 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| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.6745e+00| 4.464829| 7.431942| 7.458154| 9.933935| -0.021870| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.6698e+00| 4.631801| 7.372252| 7.315231| 10.064444| -0.016898| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.6811e+00| 4.753740| 7.478673| 7.380864| 10.292131| -0.024022| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.6874e+00| 4.917891| 7.608523| 7.447672| 10.376358| -0.020319| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.6884e+00| 4.935340| 7.615357| 7.520516| 10.436208| -0.015719| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 4.93534| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelastic_Iterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |CSV file |surface_flow_aeroelastic_Iterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary |flow_aeroelastic_Iterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). |Tecplot binary surface |surface_flow_aeroelastic_Iterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelastic_Iterative.dat). +-----------------------------------------------------------------------+ Warning: there are 1485 non-physical points in the solution. Warning: 743 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Executing dataTransfer "Pressure"...... Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 9800 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 9800 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 16 Number of data points = 9800 Running PreAnalysis ...... astros Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 330 (total = 330) Extracting external pressure loads from data transfer.... TransferName = Skin_Bottom Number of Elements = 330 (total = 660) Extracting external pressure loads from data transfer.... TransferName = Skin_Tip Number of Elements = 30 (total = 690) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Running Astros...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL Running PostAnalysis ...... astros WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'! WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'! WARNING: 'capsAnalysis.getAnalysisInfo' is deprecated. Please use 'Analysis.info'! WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'! WARNING: 'capsBound.fillVertexSets' is deprecated. Please use 'None'! WARNING: 'capsBound.executeTransfer' is deprecated. Please use 'None'! WARNING: 'capsBound.getDestData' is deprecated. Please use 'vertexSet["name"].dataSet["variableName"].getData'! WARNING: 'DataSet.getData' is deprecated. Please use 'DataSet.data'! WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'! real 1m56.388s user 1m45.333s sys 0m11.181s + status=0 + set +x ================================================= Legacy CAPS verification (using pyCAPS) case aeroelastic_Iterative_SU2_and_Astros.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Legacy Did not run examples for: Mystran ================================================= All tests pass! ================================================= ================================================= [Execution node] check if [macys] is in [[windows10x64]] Run condition [Execution node ] preventing perform for step [Execute Windows batch command] [GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64') [GNU C Compiler (gcc)] Successfully parsed console log [GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates) [GNU C Compiler (gcc)] Skipping post processing [GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues [GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Successfully parsed console log [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64') [Clang] Skipping post processing [Clang] No filter has been set, publishing all 0 issues [Clang] Repository miner is not configured, skipping repository mining [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64') [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/AEROELASTIC/DARWIN64') [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Reference build recorder is not configured [Static Analysis] No valid reference build found [Static Analysis] All reported issues will be considered outstanding [Static Analysis] No quality gates have been set - skipping [Static Analysis] Health report is disabled - skipping [Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues) [Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_RegCaps/CASREV=7.8,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=DARWIN64,buildnode=macys #633'. [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