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Full Log| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.5190e-01| -1.204623| 1.222953| 0.850207| 4.246724| 0.464898| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.20462| < -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). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 3.094296e+09, tgt = 3.094296e+09, diff = 2.761478e-01 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 3.012701e+09, tgt = 3.012701e+09, diff = 9.259372e+01 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 4.100735e+07, tgt = 4.100735e+07, diff = 0.000000e+00 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 8 (total = 8) TransferName = Skin_Bottom Number of Elements = 8 (total = 16) TransferName = Skin_Tip Number of Elements = 2 (total = 18) Writing 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 Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG 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 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_0.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: aeroelasticSimple_Iterative.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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). ----------------------- Write deformed grid files ----------------------- |SU2 mesh |aeroelasticSimple_Iterative.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Solver Postprocessing ------------------------- Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. Completed in 1.940432 seconds on 1 core. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: ../aflr3/aflr3_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative.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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 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: 50.9602. Mean K: 0.840771. Standard deviation K: 3.91674. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 54.7347| 85.2677| | CV Face Area Aspect Ratio| 1.19952| 19.2647| | CV Sub-Volume Ratio| 1| 10.0465| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11890| 1/1.00| 10| | 1| 2113| 1/5.63| 8.43329| | 2| 437| 1/4.84| 7.48082| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 8.34786 m^2. Area projection in the x-plane = 0.588155 m^2, y-plane = 0.276999 m^2, z-plane = 3.94869 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380417 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.85958e-18 m, z-direction = -0.0467006 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| 2.7977e-01| -0.835286| 1.476406| 1.165337| 4.633820| -1.015531| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.7707e-01| -1.154927| 1.365414| 1.024675| 4.297329| -0.649165| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.9354e-01| -1.204623| 1.222953| 0.850207| 4.246724| 0.464898| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.20462| < -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). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 3.094296e+09, tgt = 3.094296e+09, diff = 2.761478e-01 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 3.012701e+09, tgt = 3.012701e+09, diff = 9.259372e+01 Reading SU2 AeroLoad File - surface_flow_aeroelasticSimple_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 4.100735e+07, tgt = 4.100735e+07, diff = 0.000000e+00 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 8 (total = 8) TransferName = Skin_Bottom Number of Elements = 8 (total = 16) TransferName = Skin_Tip Number of Elements = 2 (total = 18) Writing 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 Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG 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 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_0.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: aeroelasticSimple_Iterative.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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). ----------------------- Write deformed grid files ----------------------- |SU2 mesh |aeroelasticSimple_Iterative.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Solver Postprocessing ------------------------- Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. Completed in 1.862544 seconds on 1 core. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: ../aflr3/aflr3_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticSimple_Iterative.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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 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: 50.9602. Mean K: 0.840771. Standard deviation K: 3.91674. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 54.7347| 85.2677| | CV Face Area Aspect Ratio| 1.19952| 19.2647| | CV Sub-Volume Ratio| 1| 10.0465| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11890| 1/1.00| 10| | 1| 2113| 1/5.63| 8.43329| | 2| 437| 1/4.84| 7.48082| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 8.34786 m^2. Area projection in the x-plane = 0.588155 m^2, y-plane = 0.276999 m^2, z-plane = 3.94869 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380417 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.85958e-18 m, z-direction = -0.0467006 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| 3.1261e-01| -0.835286| 1.476406| 1.165337| 4.633820| -1.015531| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.1052e-01| -1.154927| 1.365414| 1.024675| 4.297329| -0.649165| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.0589e-01| -1.204623| 1.222953| 0.850207| 4.246724| 0.464898| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.20462| < -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). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Cl = 0.094691 Cd = 0.203681 real 0m21.459s user 0m19.120s sys 0m2.608s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelasticSimple_Iterative_SU2_and_Astros.py passed (as expected) ================================================= ================================================= + echo 'aeroelastic_Iterative_SU2_and_Astros.py test;' + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt aeroelastic_Iterative_SU2_and_Astros.py test; + tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/DARWIN_ARM64/ESP/DARWIN_ARM64/examples/regressionTest/pyCAPSlog.txt + python -u aeroelastic_Iterative_SU2_and_Astros.py -outLevel=0 Running PreAnalysis ...... su2 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.14.6 AFLR2 : Version Date 11/20/22 @ 09:21PM AFLR2 : Compile OS Darwin 22.3.0 arm64 AFLR2 : Compile Date 03/08/23 @ 05:04PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.4.5 AFLR4 : Version Date 04/20/23 @ 05:37PM AFLR4 : Compile OS Darwin 22.4.0 arm64 AFLR4 : Compile Date 04/20/23 @ 05:37PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.24 EGADS : OpenCASCADE Version 7.6.0 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 1 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 9 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 12 Nodes EGADS : Check Grid BCs EGADS : Grid BCs are OK EGADS : Face Neighbor-Faces Information EGADS : QC = Face Quad Combination Flag EGADS : IER = Face Isolated Edge Refinement Flag EGADS : ER = Face Edge Refinement Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : SF = Face Scale Factor EGADS : Not applicable for Faces with a FarField Grid BC. EGADS : Face Body QC IER ER Scale Neighbor EGADS : ID Active ID Flag Flag Weight Factor Faces EGADS : 1 Yes 0 0 1 0 1 2 3 4 5 EGADS : 2 Yes 0 0 1 0 1 1 3 5 6 EGADS : 3 Yes 0 0 1 0 1 1 2 4 6 7 8 EGADS : 4 Yes 0 0 1 0 1 1 3 5 6 EGADS : 5 Yes 0 0 1 0 1 1 2 4 6 EGADS : 6 Yes 0 0 1 0 1 2 3 4 5 EGADS : 7 Yes 0 0 1 0 1 3 8 9 EGADS : 8 Yes 0 0 1 0 1 3 7 9 EGADS : 9 Yes 0 0 1 0 1 7 8 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 1 2 -3 -4 EGADS : 2 5 6 -7 -1 EGADS : 3 -2 7 9 -8 -10 -11 EGADS : 4 -12 3 8 -13 EGADS : 5 4 12 -14 -5 EGADS : 6 -6 14 13 -9 EGADS : 7 15 10 -17 -16 EGADS : 8 17 11 -15 -18 EGADS : 9 16 18 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 4 EGADS : 4 5 EGADS : 5 6 EGADS : 6 7 EGADS : 7 8 EGADS : 8 9 EGADS : 9 10 EGADS : Loop Edges Information EGADS : Loop Active Sense Edges EGADS : 1 Yes 1 1 2 -3 -4 EGADS : 2 Yes 1 5 6 -7 -1 EGADS : 3 Yes 1 -2 7 9 -8 EGADS : 4 Yes 1 -10 -11 EGADS : 5 Yes 1 -12 3 8 -13 EGADS : 6 Yes 1 4 12 -14 -5 EGADS : 7 Yes 1 -6 14 13 -9 EGADS : 8 Yes 1 15 10 -17 -16 EGADS : 9 Yes 1 17 11 -15 -18 EGADS : 10 Yes 1 16 18 EGADS : Edge Node, Scale Factor, and Neighbor-Faces Information EGADS : ESF = Edge Scale Factor EGADS : Not applicable for DEGENERATE Edges or Edges with a FarField EGADS : Grid BC Neighbor Face. EGADS : Neighbor EGADS : Edge Body Active Node1 Node2 ESF Faces EGADS : 1 0 Yes 2 1 1 1 2 EGADS : 2 0 Yes 1 3 1 1 3 EGADS : 3 0 Yes 4 3 1 1 4 EGADS : 4 0 Yes 2 4 1 1 5 EGADS : 5 0 Yes 2 5 1 2 5 EGADS : 6 0 Yes 5 6 1 2 6 EGADS : 7 0 Yes 1 6 1 2 3 EGADS : 8 0 Yes 3 7 1 3 4 EGADS : 9 0 Yes 6 7 1 3 6 EGADS : 10 0 Yes 8 9 1 3 7 EGADS : 11 0 Yes 9 8 1 3 8 EGADS : 12 0 Yes 4 10 1 4 5 EGADS : 13 0 Yes 10 7 1 4 6 EGADS : 14 0 Yes 5 10 1 5 6 EGADS : 15 0 Yes 11 8 1 7 8 EGADS : 16 0 Yes 11 12 1 7 9 EGADS : 17 0 Yes 12 9 1 7 8 EGADS : 18 0 Yes 12 11 1 8 9 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 0 0 0 EGADS : 2 Yes 0 40 0 EGADS : 3 Yes 0 0 20 EGADS : 4 Yes 0 40 20 EGADS : 5 Yes 20 40 0 EGADS : 6 Yes 20 0 0 EGADS : 7 Yes 20 0 20 EGADS : 8 Yes 1.61374306 0 0 EGADS : 9 Yes 0 0 0 EGADS : 10 Yes 20 40 20 EGADS : 11 Yes 2.53650745 3.87298335 0.334116517 EGADS : 12 Yes 1.57194608 3.87298335 0.249728332 EGADS : Face and Edge Match Information EGADS : No Face Matches Found EGADS : No Edge Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 40 AFLR4 : Min Bounding Box Length = 40 AFLR4 : Max Ref Bounding Box Length = 40 AFLR4 : Min Ref Bounding Box Length = 40 AFLR4 : Reference Length = 3.22749 AFLR4 : BL Thickness = 0 AFLR4 : Abs Min Surf Spacing = 0.00806872 AFLR4 : Min Surf Spacing = 0.322749 AFLR4 : Max Surf Spacing = 2.42061 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 STD w/BL AFLR4 : 8 CAD geometry 0 STD w/BL AFLR4 : 9 CAD geometry 0 STD w/BL AFLR4 : Define CAD surface definition 1 AFLR4 : Define CAD surface definition 2 AFLR4 : Define CAD surface definition 3 AFLR4 : Define CAD surface definition 4 AFLR4 : Define CAD surface definition 5 AFLR4 : Define CAD surface definition 6 AFLR4 : Define CAD surface definition 7 AFLR4 : Define CAD surface definition 8 AFLR4 : Define CAD surface definition 9 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 376 682 0 AFLR4 : Nodes, Trias,Quads= 381 692 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 374 678 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 984 1890 0 AFLR4 : Nodes, Trias,Quads= 852 1626 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 376 682 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 374 678 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 376 682 0 AFLR4 : Nodes, Trias,Quads= 378 686 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 91 147 0 AFLR4 : Nodes, Trias,Quads= 72 109 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 89 142 0 AFLR4 : Nodes, Trias,Quads= 70 104 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 11 13 0 AFLR4 : Nodes, Trias,Quads= 7 5 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 2648 5292 492 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 2648 5292 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 386 702 0 AFLR4 : Nodes, Trias,Quads= 380 690 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 382 694 0 AFLR4 : Nodes, Trias,Quads= 381 692 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 1077 2074 0 AFLR4 : Nodes, Trias,Quads= 1011 1942 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 383 696 0 AFLR4 : Nodes, Trias,Quads= 379 688 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 383 696 0 AFLR4 : Nodes, Trias,Quads= 382 694 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 383 696 0 AFLR4 : Nodes, Trias,Quads= 379 688 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 99 160 0 AFLR4 : Nodes, Trias,Quads= 81 124 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 96 154 0 AFLR4 : Nodes, Trias,Quads= 77 116 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 11 12 0 AFLR4 : Nodes, Trias,Quads= 8 6 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 2822 5640 500 OVERALL : CPU Time = 0.129 seconds Body 1 (of 1) Number of nodes = 2822 Number of elements = 5640 Number of node elements = 0 Number of line elements = 0 Number of triangle elements = 5640 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 2822 Total number of elements = 5640 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Farfield, index = 1 Name = SymmPlane, index = 2 Name = Skin, index = 3 Getting volume mesh AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.14.6 AFLR2 : Version Date 11/20/22 @ 09:21PM AFLR2 : Compile OS Darwin 22.3.0 arm64 AFLR2 : Compile Date 03/08/23 @ 05:04PM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.4.5 AFLR4 : Version Date 04/20/23 @ 05:37PM AFLR4 : Compile OS Darwin 22.4.0 arm64 AFLR4 : Compile Date 04/20/23 @ 05:37PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.24 EGADS : OpenCASCADE Version 7.6.0 EGADS : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.24 EGADS : OpenCASCADE Version 7.6.0 EGADS : --------------------------------------- Volume mesh: Number of nodes = 11890 Number of elements = 67404 Number of triangles = 5640 Number of quadrilatarals = 0 Number of tetrahedrals = 61764 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 No project name ("Proj_Name") provided - A volume mesh will not be written out 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 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: ../aflr3/aflr3_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 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: 50.9602. Mean K: 0.840771. Standard deviation K: 3.91674. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 54.7347| 85.2677| | CV Face Area Aspect Ratio| 1.19952| 19.2647| | CV Sub-Volume Ratio| 1| 10.0465| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11890| 1/1.00| 10| | 1| 2113| 1/5.63| 8.43329| | 2| 437| 1/4.84| 7.48082| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 8.34786 m^2. Area projection in the x-plane = 0.588155 m^2, y-plane = 0.276999 m^2, z-plane = 3.94869 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380417 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.85958e-18 m, z-direction = -0.0467006 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| 3.1124e-01| -0.835286| 1.476406| 1.165337| 4.633820| -1.015531| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.0913e-01| -1.154927| 1.365414| 1.024675| 4.297329| -0.649165| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.1335e-01| -1.204623| 1.222953| 0.850207| 4.246724| 0.464898| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.20462| < -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). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = Rib_Root, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 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 Creating FEA BEM Getting quads for BEM! Mesh for body = 0 Number of nodal coordinates = 131 Number of elements = 188 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 40 Elemental Quad4 = 148 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 = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 3.094296e+09, tgt = 3.094296e+09, diff = 7.142196e+01 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 3.012701e+09, tgt = 3.012701e+09, diff = 4.552938e+01 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 4.100735e+07, tgt = 4.100735e+07, diff = 4.732293e+00 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 48 (total = 48) TransferName = Skin_Bottom Number of Elements = 48 (total = 96) TransferName = Skin_Tip Number of Elements = 12 (total = 108) 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 Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG 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 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_0.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: aeroelastic_Iterative.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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). ----------------------- Write deformed grid files ----------------------- |SU2 mesh |aeroelastic_Iterative.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Solver Postprocessing ------------------------- Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. Completed in 2.340899 seconds on 1 core. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: ../aflr3/aflr3_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 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: 50.9602. Mean K: 0.840771. Standard deviation K: 3.91674. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 54.7347| 85.2677| | CV Face Area Aspect Ratio| 1.19952| 19.2647| | CV Sub-Volume Ratio| 1| 10.0465| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11890| 1/1.00| 10| | 1| 2113| 1/5.63| 8.43329| | 2| 437| 1/4.84| 7.48082| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 8.34786 m^2. Area projection in the x-plane = 0.588155 m^2, y-plane = 0.276999 m^2, z-plane = 3.94869 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380417 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.85958e-18 m, z-direction = -0.0467006 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| 2.3903e-01| -0.835286| 1.476406| 1.165337| 4.633820| -1.015531| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.6064e-01| -1.154927| 1.365414| 1.024675| 4.297329| -0.649165| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.7243e-01| -1.204623| 1.222953| 0.850207| 4.246724| 0.464898| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.20462| < -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). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 3.094296e+09, tgt = 3.094296e+09, diff = 7.142196e+01 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 3.012701e+09, tgt = 3.012701e+09, diff = 4.552938e+01 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 4.100735e+07, tgt = 4.100735e+07, diff = 4.732293e+00 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 48 (total = 48) TransferName = Skin_Bottom Number of Elements = 48 (total = 96) TransferName = Skin_Tip Number of Elements = 12 (total = 108) 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 Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG 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 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_0.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: aeroelastic_Iterative.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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). ----------------------- Write deformed grid files ----------------------- |SU2 mesh |aeroelastic_Iterative.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Solver Postprocessing ------------------------- Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. Completed in 2.384434 seconds on 1 core. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: ../aflr3/aflr3_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 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: 50.9602. Mean K: 0.840771. Standard deviation K: 3.91674. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 54.7347| 85.2677| | CV Face Area Aspect Ratio| 1.19952| 19.2647| | CV Sub-Volume Ratio| 1| 10.0465| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11890| 1/1.00| 10| | 1| 2113| 1/5.63| 8.43329| | 2| 437| 1/4.84| 7.48082| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 8.34786 m^2. Area projection in the x-plane = 0.588155 m^2, y-plane = 0.276999 m^2, z-plane = 3.94869 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380417 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.85958e-18 m, z-direction = -0.0467006 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| 3.0135e-01| -0.835286| 1.476406| 1.165337| 4.633820| -1.015531| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.7320e-01| -1.154927| 1.365414| 1.024675| 4.297329| -0.649165| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.7094e-01| -1.204623| 1.222953| 0.850207| 4.246724| 0.464898| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.20462| < -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). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 Running PreAnalysis ...... su2 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Top' Normalized Integrated 'Pressure' Rank 0: src = 3.094296e+09, tgt = 3.094296e+09, diff = 7.142196e+01 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Bottom' Normalized Integrated 'Pressure' Rank 0: src = 3.012701e+09, tgt = 3.012701e+09, diff = 4.552938e+01 Reading SU2 AeroLoad File - surface_flow_aeroelastic_Iterative.csv Number of variables = 13 Number of data points = 130 CAPS Info: Bound 'Skin_Tip' Normalized Integrated 'Pressure' Rank 0: src = 4.100735e+07, tgt = 4.100735e+07, diff = 4.732293e+00 Extracting external pressure loads from data transfer.... TransferName = Skin_Top Number of Elements = 48 (total = 48) TransferName = Skin_Bottom Number of Elements = 48 (total = 96) TransferName = Skin_Tip Number of Elements = 12 (total = 108) 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 Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG 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 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../aflr3/aflr3_0.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: aeroelastic_Iterative.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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 tetrahedra. ----------------------- Preprocessing computations ---------------------- Setting local point connectivity. Checking the numerical grid orientation of the interior elements. All volume elements are correctly orientend. All surface elements are correctly orientend. Identify edges and vertices. Setting the bound control volume structure. Volume of the computational grid: 63999.5. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). ----------------------- Write deformed grid files ----------------------- |SU2 mesh |aeroelastic_Iterative.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Solver Postprocessing ------------------------- Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. Completed in 2.320319 seconds on 1 core. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 7.5.1 "Blackbird" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, 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: ../aflr3/aflr3_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 3. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_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. 11890 grid points. 61764 volume elements. 3 surface markers. 3452 boundary elements in index 0 (Marker = BC_1). 1942 boundary elements in index 1 (Marker = BC_2). 246 boundary elements in index 2 (Marker = BC_3). 61764 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: 50.9602. Mean K: 0.840771. Standard deviation K: 3.91674. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 54.7347| 85.2677| | CV Face Area Aspect Ratio| 1.19952| 19.2647| | CV Sub-Volume Ratio| 1| 10.0465| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 11890| 1/1.00| 10| | 1| 2113| 1/5.63| 8.43329| | 2| 437| 1/4.84| 7.48082| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 8.34786 m^2. Area projection in the x-plane = 0.588155 m^2, y-plane = 0.276999 m^2, z-plane = 3.94869 m^2. Max. coordinate in the x-direction = 2.53651 m, y-direction = 3.87298 m, z-direction = 0.380417 m. Min. coordinate in the x-direction = 0 m, y-direction = -2.85958e-18 m, z-direction = -0.0467006 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| 2.9499e-01| -0.835286| 1.476406| 1.165337| 4.633820| -1.015531| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.0604e-01| -1.154927| 1.365414| 1.024675| 4.297329| -0.649165| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.0378e-01| -1.204623| 1.222953| 0.850207| 4.246724| 0.464898| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 3) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.20462| < -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). +-----------------------------------------------------------------------+ ------------------------- Solver Postprocessing ------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ Running PostAnalysis ...... su2 real 0m43.417s user 0m53.150s sys 0m5.149s + status=0 + set +x ================================================= CAPS verification (using pyCAPS) case aeroelastic_Iterative_SU2_and_Astros.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Did not run examples for: Mystran ================================================= All tests pass! ================================================= ================================================= [GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/DARWIN_ARM64') [GNU C Compiler (gcc)] Successfully parsed console log [GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates) [GNU C Compiler (gcc)] Skipping post processing [GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues [GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/DARWIN_ARM64') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/DARWIN_ARM64') [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Successfully parsed console log [Clang] -> found 0 issues (skipped 0 duplicates) [Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/DARWIN_ARM64') [Clang] Skipping post processing [Clang] No filter has been set, publishing all 0 issues [Clang] Repository miner is not configured, skipping repository mining [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/DARWIN_ARM64') [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Successfully parsed console log [Static Analysis] -> found 0 issues (skipped 0 duplicates) [Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/AEROELASTIC/DARWIN_ARM64') [Static Analysis] Skipping post processing [Static Analysis] No filter has been set, publishing all 0 issues [Static Analysis] Repository miner is not configured, skipping repository mining [Static Analysis] Reference build recorder is not configured [Static Analysis] Obtaining reference build from same job (7.6,CAPS/AEROELASTIC,DARWIN_ARM64,viggen) [Static Analysis] Using reference build 'ESP_UndefinedCaps/CASREV=7.6,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=DARWIN_ARM64,buildnode=viggen #183' to compute new, fixed, and outstanding issues [Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0 [Static Analysis] Evaluating quality gates [Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1 [Static Analysis] -> All quality gates have been passed [Static Analysis] Health report is disabled - skipping [Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues) [Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_UndefinedCaps/CASREV=7.6,ESPTEST=CAPS/AEROELASTIC,ESP_ARCH=DARWIN_ARM64,buildnode=viggen #184'. [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