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Full LogAFLR3 QI : Nodes, Elements = 5317 13830 AFLR3 : CPU Time = 0.253 seconds AFLR3 QRG: QUALITY GRID RE-GENERATION AFLR3 QRG: Nodes, Elements = 5317 13830 AFLR3 : CPU Time = 0.006 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 13830 UG3 : Min, Max Ang = 0.006596 179.7 UG3 : Average Angle = 73.4 UG3 : No. Angle>160.0 = 1922 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 13830 UG3 : Min Vol = 0.000293 UG3 : Average Vol = 4.31e+06 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol<TOL = 0 UG3 : Q VOL-LENGTH-RATIO CHECK 2/3 2 UG3 : Q = c * Vol / sum( L ) UG3 : 0 <= Q <= 1 UG3 : No. Tet Elems = 13830 UG3 : Min, Max Q = 1.25e-05 1 UG3 : Average Q = 0.106 UG3 : No. Q< 0.1 = 10496 UG3 : No. Q< 0.01 = 8943 OVERALL : CPU Time = 0.474 seconds UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 13830 UG3 : Min, Max Ang = 0.006596 179.7 UG3 : Average Angle = 73.4 UG3 : No. Angle>160.0 = 1922 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 13830 UG3 : Min Vol = 0.000293 UG3 : Average Vol = 4.31e+06 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol<TOL = 0 UG3 : Q VOL-LENGTH-RATIO CHECK 2/3 2 UG3 : Q = c * Vol / sum( L ) UG3 : 0 <= Q <= 1 UG3 : Note that L includes scaling for BL-aspect=ratio UG3 : No. Tet Elems = 13830 UG3 : Min, Max Q = 0.0034 1 UG3 : Average Q = 0.186 UG3 : No. Q< 0.1 = 8713 UG3 : No. Q< 0.01 = 59 UG3 : CPU Time = 0.000 seconds EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.0 EGADS : --------------------------------------- EGADS : CREATE EGADS TESS FROM AFLR3 DATA EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 1 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 2 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 3 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 4 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 5 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 6 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 7 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 8 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 9 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 10 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 11 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 12 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 13 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 14 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 15 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 16 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 17 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 18 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 1 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 2 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 3 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 4 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 5 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 6 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 7 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 8 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 9 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 10 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 19 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 20 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 21 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 22 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 23 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 24 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 25 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 26 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 27 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 28 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 29 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 30 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 11 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 12 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 13 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 14 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 15 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 16 EGADS : EGADS TESS CREATED EGADS : CHECK TESS FACE NODE MAP EGADS : CHECKING NODE MAP FOR BODY 0 FACE 1 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 2 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 3 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 4 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 5 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 6 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 7 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 8 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 9 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 10 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 11 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 12 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 13 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 14 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 15 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 16 Volume mesh: Number of nodes = 5317 Number of elements = 23688 Number of triangles = 9858 Number of quadrilatarals = 0 Number of tetrahedrals = 13830 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing Done getting CFD boundary conditions Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.5. Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 4240 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 195.346 m. Reference origin for moment evaluation is (55.4263, 0, 0). Surface(s) where the force coefficients are evaluated: BC_1. Surface(s) plotted in the output file: BC_1. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 10. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-8. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_inviscidWing.dat. Surface file name: surface_flow_inviscidWing. Volume file name: flow_inviscidWing. Restart file name: restart_flow_inviscidWing.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | Far-field| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 5317 grid points. 13830 volume elements. 2 surface markers. 9846 boundary elements in index 0 (Marker = BC_1). 12 boundary elements in index 1 (Marker = BC_2). 13830 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: 5.96352e+10. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 17.3483. Mean K: 1.87862. Standard deviation K: 2.72111. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 2.51936| 87.7801| | CV Face Area Aspect Ratio| 1.28339| 2.80217e+07| | CV Sub-Volume Ratio| 1.04782| 3.92559e+08| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 5317| 1/1.00| 10| | 1| 1307| 1/4.07| 9.39639| | 2| 226| 1/5.78| 7.85229| +-------------------------------------------+ Finding max control volume width. Semi-span length = 97.6729 m. Wetted area = 8234.67 m^2. Area projection in the x-plane = 668.083 m^2, y-plane = 415.155 m^2, z-plane = 3916.84 m^2. Max. coordinate in the x-direction = 123.552 m, y-direction = 97.6729 m, z-direction = 4.71806 m. Min. coordinate in the x-direction = 50 m, y-direction = -97.6729 m, z-direction = -8.4717 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 221265| 1| m^2/s^2| 221265| | Velocity-X| 170.123| 1| m/s| 170.123| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 2.9695| 1| m/s| 2.9695| | Velocity Magnitude| 170.149| 1| m/s| 170.149| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.5| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.3186e-01| 2.023460| 4.397129| 3.783010| 7.506305| 1.863179| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.2783e-01| 4.298015| 6.714837| 6.542729| 9.789782| 2.132951| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.2689e-01| 4.727771| 7.148676| 6.733970| 10.230267| 2.515644| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.2710e-01| 4.773027| 7.165669| 7.046496| 10.260358| 2.852228| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.2714e-01| 5.045623| 7.601076| 7.458299| 10.551039| 3.202407| | 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.2741e-01| 5.480149| 8.071079| 7.881620| 11.000946| 3.150787| | 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.2726e-01| 5.923301| 8.498020| 8.321209| 11.442224| 3.961853| | 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.2672e-01| 6.372453| 8.936643| 8.772539| 11.885227| 2.522149| | 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.2684e-01| 6.808587| 9.391142| 9.225137| 12.333941| 17.477646| | 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.2680e-01| 7.352488| 9.860621| 9.802983| 12.785819| 61.507480| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 10) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 7.35249| < -8| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_inviscidWing.dat | Writing the forces breakdown file (forces_breakdown_inviscidWing.dat). |CSV file |surface_flow_inviscidWing.csv | Writing the forces breakdown file (forces_breakdown_inviscidWing.dat). |Paraview |flow_inviscidWing.vtu | Writing the forces breakdown file (forces_breakdown_inviscidWing.dat). |Paraview surface |surface_flow_inviscidWing.vtu | Writing the forces breakdown file (forces_breakdown_inviscidWing.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ ==> Total Forces and Moments --> Cl = 1.490125 Cd = 0.024227 --> Cmx = -0.102917 Cmy = -0.21191 Cmz = -0.012195 --> Cx = -0.001783 Cy = -0.054054 Cz = 1.490321 real 0m7.284s user 0m4.583s sys 0m2.751s + status=0 + set +x ================================================= data/session08/2_su2_InviscidWing.py passed (as expected) ================================================= ================================================= 1_astros_ModalCantilever.py test; + python 1_astros_ModalCantilever.py + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Running mASTROS pre-analysis... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 425 Number of elements = 482 Number of triangle elements = 0 Number of quadrilateral elements = 482 ---------------------------- Total number of nodes = 425 Total number of elements = 482 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 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 = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 425 Number of elements = 482 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 482 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied 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 Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Writing analysis cards Writing constraint cards--all constraints for each subcase Writing material cards Writing property cards Writing coordinate system cards ==> Running mASTROS... ==> Running mASTROS post-analysis... Reading Astros OUT file - extracting Eigen-Values! Number of Eigen-Values = 10 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Loading Eigen-Value = 3 Loading Eigen-Value = 4 Loading Eigen-Value = 5 Loading Eigen-Value = 6 Loading Eigen-Value = 7 Loading Eigen-Value = 8 Loading Eigen-Value = 9 Loading Eigen-Value = 10 --> Eigen-frequencies: 1 : 0.00145606 2 : 0.0014575 3 : 0.00332859 4 : 0.00333096 5 : 0.00445176 6 : 0.00445507 7 : 0.00894917 8 : 0.0089521 9 : 0.0110353 10: 0.0110413 real 1m5.491s user 1m11.210s sys 0m36.511s + status=0 + set +x ================================================= data/session09/1_astros_ModalCantilever.py passed (as expected) ================================================= ================================================= 2_astros_ModalSupport.py test; + python 2_astros_ModalSupport.py + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Running mASTROS pre-analysis... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Name = ribSupport, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 831 Number of elements = 962 Number of triangle elements = 0 Number of quadrilateral elements = 962 Body 2 (of 2) Number of nodes = 1 Number of elements = 0 Number of triangle elements = 0 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 832 Total number of elements = 962 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = ribRootPoint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 2 Name = leftPointLoad, index = 1 Name = ritePointLoad, index = 2 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 1 Name = ribRoot, index = 1 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 = 6 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Name = ribSupport, index = 6 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 831 Number of elements = 962 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 962 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 1 Number of elements = 1 Elemental Nodes = 1 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 832 Combined Number of elements = 963 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 962 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 6 Property name - leftWingSkin Property name - ribSupport Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - ribRootPoint No "constraintType" specified for Constraint tuple ribRootPoint, defaulting to "ZeroDisplacement" No "groupName" specified for Constraint tuple ribRootPoint, going to use constraint name Done getting FEA constraints Getting FEA supports....... Number of supports - 1 Support name - ribRootPoint No "groupName" specified for Support tuple ribRootPoint, going to use support name Done getting FEA supports Getting FEA connections....... Number of connection tuples - 1 Connection name - ribRoot No "groupName" specified for Connection tuple ribRoot! Looking for automatic connections from the use of capsConnectLink for ribRoot 9 automatic connections were made for capsConnect ribRoot (node id 832) Done getting FEA connections Load tuple is NULL - No loads applied 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 Getting FEA analyses....... Number of analyses - 1 Analysis name - EigenAnalysis Done getting FEA analyses Writing Astros grid and connectivity file (in large field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing connection cards - appending mesh file Writing Astros instruction file.... Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!! Writing analysis cards Writing constraint cards--all constraints for each subcase Writing support cards Writing material cards Writing property cards Writing coordinate system cards ==> Running mASTROS... ==> Running mASTROS post-analysis... Reading Astros OUT file - extracting Eigen-Values! Number of Eigen-Values = 10 Loading Eigen-Value = 1 Loading Eigen-Value = 2 Loading Eigen-Value = 3 Loading Eigen-Value = 4 Loading Eigen-Value = 5 Loading Eigen-Value = 6 Loading Eigen-Value = 7 Loading Eigen-Value = 8 Loading Eigen-Value = 9 Loading Eigen-Value = 10 --> Eigen-frequencies: 1 : 1.93141e-08 2 : 0.0014201 3 : 0.00174471 4 : 0.00323704 5 : 0.00324327 6 : 0.00432932 7 : 0.00512433 8 : 0.00873482 9 : 0.0100619 10: 0.0107025 real 3m39.344s user 3m29.314s sys 1m32.092s + status=0 + set +x ================================================= data/session09/2_astros_ModalSupport.py passed (as expected) ================================================= ================================================= 3_astros_StaticCantilever.py test; + python 3_astros_StaticCantilever.py + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Running mASTROS pre-analysis... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 425 Number of elements = 482 Number of triangle elements = 0 Number of quadrilateral elements = 482 ---------------------------- Total number of nodes = 425 Total number of elements = 482 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 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 = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 425 Number of elements = 482 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 482 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - leftPointLoad No "groupName" specified for Load tuple leftPointLoad, going to use load name Load name - ritePointLoad No "groupName" specified for Load tuple ritePointLoad, 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 Writing Astros grid and connectivity file (in large 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 Writing coordinate system cards ==> Running mASTROS... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running mASTROS post-analysis... --> Maximum displacements: --> Tmax 238433.3403112283 --> T1max 16861.9 --> T2max 16414.9 --> T3max 237286.0 real 0m31.050s user 0m50.185s sys 0m23.216s + status=0 + set +x ================================================= data/session09/3_astros_StaticCantilever.py passed (as expected) ================================================= ================================================= 4_astros_Composite.py test; + python 4_astros_Composite.py + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle ==> Running mASTROS pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 425 Number of elements = 482 Number of triangle elements = 0 Number of quadrilateral elements = 482 ---------------------------- Total number of nodes = 425 Total number of elements = 482 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 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 = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 425 Number of elements = 482 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 482 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Aluminum No "materialType" specified for Material tuple Aluminum, defaulting to "Isotropic" Material name - Graphite_epoxy Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - leftPointLoad No "groupName" specified for Load tuple leftPointLoad, going to use load name Load name - ritePointLoad No "groupName" specified for Load tuple ritePointLoad, 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 Writing Astros grid and connectivity file (in large 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 Writing coordinate system cards ==> Running mASTROS... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running mASTROS post-analysis... --> Maximum displacements: --> Tmax 52594.60117638786 --> T1max 4359.68 --> T2max 3216.5 --> T3max 52322.2 real 0m30.469s user 0m50.037s sys 0m22.839s + status=0 + set +x ================================================= data/session09/4_astros_Composite.py passed (as expected) ================================================= [macys.mit.edu:89814] shmem: mmap: an error occurred while determining whether or not /var/folders/xs/_fh4l1p54zqcl6mbk4zclcfr0000gp/T//ompi.macys.502/jf.0/3309568000/sm_segment.macys.502.c5440000.0 could be created. ================================================= 6_tacs_StaticCantilever.py.py test; + python 6_tacs_StaticCantilever.py.py + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/CAPS/training/2023/training.log /Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/ESP/DARWIN64/bin/python: can't open file '/Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/CAPS/training/2023/data/session09/6_tacs_StaticCantilever.py.py': [Errno 2] No such file or directory real 0m0.130s user 0m0.042s sys 0m0.059s + status=2 + set +x ================================================= data/session09/6_tacs_StaticCantilever.py.py failed (as NOT expected) ================================================= ================================================= 7_tacs_sizing.py test; + python 7_tacs_sizing.py + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/CAPS/training/2023/training.log [macys.mit.edu:89842] shmem: mmap: an error occurred while determining whether or not /var/folders/xs/_fh4l1p54zqcl6mbk4zclcfr0000gp/T//ompi.macys.502/jf.0/1097203712/sm_segment.macys.502.41660000.0 could be created. ==> Loading geometry from file "../ESP/transport.csm"... ==> Starting optimization... MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 3852 Number of elements = 4061 Number of triangle elements = 0 Number of quadrilateral elements = 4061 ---------------------------- Total number of nodes = 3852 Total number of elements = 4061 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 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 = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 3852 Number of elements = 4061 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 4061 Getting FEA materials....... Number of materials - 1 Material name - aluminum Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Getting FEA loads....... Number of loads - 2 Load name - leftWingSkin No "groupName" specified for Load tuple leftWingSkin, going to use load name Load name - riteWingSkin No "groupName" specified for Load tuple riteWingSkin, going to use load name Done getting FEA loads Getting FEA design variables....... Number of design variables - 3 Design_Variable name - ribThk Design_Variable name - skinThk Design_Variable name - sparThk Design_Variable_Relation name - relLeftSkin Design_Variable_Relation name - relRib Design_Variable_Relation name - relRiteSkin Design_Variable_Relation name - relSpar Number of design variable relations - 4 Done getting FEA design variables Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Analysis tuple is NULL Getting FEA analyses....... Number of analyses - 1 Analysis name - Default Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing TACS instruction file.... Writing analysis cards Writing load ADD cards Writing constraint ADD cards Writing load cards Writing constraint cards Writing material cards Writing property cards Writing coordinate system cards Writing design variable cards Writing design variable relation cards [0] Creating TACSAssembler with numOwnedNodes = 3852 numElements = 4061 [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 /Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/CAPS/training/2023/data/session09/7_tacs_sizing.py:144: DeprecationWarning: Conversion of an array with ndim > 0 to a scalar is deprecated, and will error in future. Ensure you extract a single element from your array before performing this operation. (Deprecated NumPy 1.25.) xarray[ithick] = float(inputs[thick_dv]) --> ribThk [0.05] --> skinThk [0.003] --> sparThk [0.1] --> mass [351348.8584378] --> ks_vmfailure [0.18465374] --> mass [351348.8584378] --> ks_vmfailure [0.18465374] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00701607]] --> ks_vmfailure skinThk [[-0.77735769]] --> ks_vmfailure sparThk [[-0.00419852]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.001] --> skinThk [0.00739074] --> sparThk [0.001] --> mass [164778.06753421] --> ks_vmfailure [0.18458271] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.27193778]] --> ks_vmfailure skinThk [[-0.30939956]] --> ks_vmfailure sparThk [[-0.20978605]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.001] --> skinThk [0.001] --> sparThk [0.02273644] --> mass [129232.41385728] --> ks_vmfailure [0.20239501] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.001] --> skinThk [0.00647627] --> sparThk [0.00411034] --> mass [159691.72878047] --> ks_vmfailure [0.18468723] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.28428467]] --> ks_vmfailure skinThk [[-0.36623707]] --> ks_vmfailure sparThk [[-0.04561164]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.01797054] --> skinThk [0.001] --> sparThk [0.0012247] --> mass [135761.31599909] --> ks_vmfailure [0.20097431] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00336292] --> skinThk [0.00571377] --> sparThk [0.00370855] --> mass [156359.73995058] --> ks_vmfailure [0.18476613] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.04724024]] --> ks_vmfailure skinThk [[-0.42968567]] --> ks_vmfailure sparThk [[-0.05558717]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00375419] --> skinThk [0.0118629] --> sparThk [0.00560564] --> mass [221348.46889819] --> ks_vmfailure [0.18335024] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00340205] --> skinThk [0.00632869] --> sparThk [0.00389826] --> mass [162858.61284534] --> ks_vmfailure [0.18451389] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.0033671] --> skinThk [0.00577947] --> sparThk [0.00372882] --> mass [157054.09556222] --> ks_vmfailure [0.18473688] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.04660765]] --> ks_vmfailure skinThk [[-0.42085611]] --> ks_vmfailure sparThk [[-0.05458697]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.001] --> skinThk [0.0114244] --> sparThk [0.01236645] --> mass [220187.17438764] --> ks_vmfailure [0.18349008] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.22376308]] --> ks_vmfailure skinThk [[-0.11542908]] --> ks_vmfailure sparThk [[-0.00924893]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00726772] --> skinThk [0.01192034] --> sparThk [0.01564752] --> mass [242329.88574404] --> ks_vmfailure [0.18318718] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00374643] --> skinThk [0.01164171] --> sparThk [0.01380417] --> mass [229889.80169957] --> ks_vmfailure [0.18327675] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.0024241] --> skinThk [0.01153708] --> sparThk [0.01311195] --> mass [225218.2736428] --> ks_vmfailure [0.18333401] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.04342337]] --> ks_vmfailure skinThk [[-0.10932276]] --> ks_vmfailure sparThk [[-0.00862543]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00273423] --> skinThk [0.02300858] --> sparThk [0.0208162] --> mass [351071.64335651] --> ks_vmfailure [0.18265072] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00246133] --> skinThk [0.01291395] --> sparThk [0.01403666] --> mass [240323.86796358] --> ks_vmfailure [0.18319035] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.04030186]] --> ks_vmfailure skinThk [[-0.08766022]] --> ks_vmfailure sparThk [[-0.00725048]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00615236] --> skinThk [0.02577931] --> sparThk [0.00214916] --> mass [361343.31744605] --> ks_vmfailure [0.18263733] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00640621]] --> ks_vmfailure skinThk [[-0.02501965]] --> ks_vmfailure sparThk [[-0.04131297]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00713229] --> skinThk [0.02677305] --> sparThk [0.0168223] --> mass [392609.86291328] --> ks_vmfailure [0.18251681] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00663017] --> skinThk [0.02626385] --> sparThk [0.00930372] --> mass [376588.76116566] --> ks_vmfailure [0.18255199] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.0064128] --> skinThk [0.02604342] --> sparThk [0.00604892] --> mass [369653.21087943] --> ks_vmfailure [0.18257185] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00605012]] --> ks_vmfailure skinThk [[-0.02434576]] --> ks_vmfailure sparThk [[-0.00555063]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.0097372] --> skinThk [0.04835412] --> sparThk [0.00759194] --> mass [602336.93932585] --> ks_vmfailure [0.18225672] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.00752075] --> skinThk [0.03347906] --> sparThk [0.00656318] --> mass [447201.32423534] --> ks_vmfailure [0.18242234] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00423673]] --> ks_vmfailure skinThk [[-0.01486475]] --> ks_vmfailure sparThk [[-0.00451743]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.01240423] --> skinThk [0.05849094] --> sparThk [0.01317201] --> mass [716841.47781672] --> ks_vmfailure [0.18217976] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00154606]] --> ks_vmfailure skinThk [[-0.00498155]] --> ks_vmfailure sparThk [[-0.00115575]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.01929414] --> skinThk [0.09078555] --> sparThk [0.02029672] --> mass [1064340.58921378] --> ks_vmfailure [0.18206339] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00064649]] --> ks_vmfailure skinThk [[-0.00208485]] --> ks_vmfailure sparThk [[-0.00048511]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.02545586] --> skinThk [0.11766696] --> sparThk [0.02722908] --> mass [1355784.09501524] --> ks_vmfailure [0.18201458] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.0003768]] --> ks_vmfailure skinThk [[-0.00124124]] --> ks_vmfailure sparThk [[-0.00027327]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.02816247] --> skinThk [0.1278486] --> sparThk [0.03061507] --> mass [1467935.54338862] --> ks_vmfailure [0.1820012] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00031099]] --> ks_vmfailure skinThk [[-0.00105064]] --> ks_vmfailure sparThk [[-0.00021913]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.02874638] --> skinThk [0.12860072] --> sparThk [0.03166063] --> mass [1478053.22646291] --> ks_vmfailure [0.18200001] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00030043]] --> ks_vmfailure skinThk [[-0.00103744]] --> ks_vmfailure sparThk [[-0.00020726]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.02995584] --> skinThk [0.12773274] --> sparThk [0.03432163] --> mass [1475323.18211848] --> ks_vmfailure [0.18200005] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00028252]] --> ks_vmfailure skinThk [[-0.00104812]] --> ks_vmfailure sparThk [[-0.000184]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03300207] --> skinThk [0.12582909] --> sparThk [0.0407494] --> mass [1470920.60962544] --> ks_vmfailure [0.18200021] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00024502]] --> ks_vmfailure skinThk [[-0.00107038]] --> ks_vmfailure sparThk [[-0.00014848]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03417052] --> skinThk [0.12543856] --> sparThk [0.04303502] --> mass [1472403.19847778] --> ks_vmfailure [0.18200002] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00023279]] --> ks_vmfailure skinThk [[-0.00107335]] --> ks_vmfailure sparThk [[-0.00014019]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03466537] --> skinThk [0.12523006] --> sparThk [0.04393562] --> mass [1472509.9882878] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022797]] --> ks_vmfailure skinThk [[-0.00107536]] --> ks_vmfailure sparThk [[-0.00013746]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03477343] --> skinThk [0.12519386] --> sparThk [0.04405893] --> mass [1472530.53633059] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022693]] --> ks_vmfailure skinThk [[-0.00107573]] --> ks_vmfailure sparThk [[-0.00013712]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03499382] --> skinThk [0.12513457] --> sparThk [0.04415997] --> mass [1472520.48038099] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022479]] --> ks_vmfailure skinThk [[-0.00107642]] --> ks_vmfailure sparThk [[-0.00013689]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03528602] --> skinThk [0.12508833] --> sparThk [0.04404571] --> mass [1472505.62701918] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022196]] --> ks_vmfailure skinThk [[-0.00107708]] --> ks_vmfailure sparThk [[-0.00013735]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03554752] --> skinThk [0.12509498] --> sparThk [0.04357429] --> mass [1472488.99260686] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.0002194]] --> ks_vmfailure skinThk [[-0.0010773]] --> ks_vmfailure sparThk [[-0.00013892]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03557543] --> skinThk [0.12515336] --> sparThk [0.04308252] --> mass [1472485.57497966] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00021902]] --> ks_vmfailure skinThk [[-0.00107687]] --> ks_vmfailure sparThk [[-0.00014054]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03549811] --> skinThk [0.12518987] --> sparThk [0.04292621] --> mass [1472487.81481868] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.0002197]] --> ks_vmfailure skinThk [[-0.00107651]] --> ks_vmfailure sparThk [[-0.00014103]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03546495] --> skinThk [0.12519741] --> sparThk [0.04292079] --> mass [1472488.37514104] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022001]] --> ks_vmfailure skinThk [[-0.00107642]] --> ks_vmfailure sparThk [[-0.00014104]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03546229] --> skinThk [0.12519748] --> sparThk [0.04292444] --> mass [1472488.42506508] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022004]] --> ks_vmfailure skinThk [[-0.00107641]] --> ks_vmfailure sparThk [[-0.00014103]] [0] BCSRMat: ILU(1000) Input fill ratio 20.00, actual fill ratio: 5.76, nnz(ILU) = 206656 --> ribThk [0.03546228] --> skinThk [0.12519745] --> sparThk [0.0429247] --> mass [1472488.42560328] --> ks_vmfailure [0.182] --> mass ribThk [[2050883.76812598]] --> mass skinThk [[10032748.6549307]] --> mass sparThk [[1314431.32692686]] --> ks_vmfailure ribThk [[-0.00022004]] --> ks_vmfailure skinThk [[-0.00107641]] --> ks_vmfailure sparThk [[-0.00014103]] Optimization terminated successfully (Exit mode 0) Current function value: 4.2071097874379575 Iterations: 29 Function evaluations: 39 Gradient evaluations: 29 Optimization Complete ----------------------------------- ==> Optimized value: --> ribThk [0.03546228] --> skinThk [0.12519745] --> sparThk [0.0429247] real 1m36.757s user 1m55.229s sys 0m27.000s + status=0 + set +x ================================================= data/session09/7_tacs_sizing.py passed (as expected) ================================================= ================================================= 2_aeroelastic_Iterative_SU2_Astros.py test; + python 2_aeroelastic_Iterative_SU2_Astros.py + tee -a /Users/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/DARWIN64/CAPS/training/2023/training.log MESSAGE:: Building wingOml MESSAGE:: Building wingWaffle ==> Running SU2 pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - leftWing Mesh sizing name - riteWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.17.15 AFLR2 : Version Date 04/23/24 @ 12:51AM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 04/23/24 @ 11:49AM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.14 AFLR4 : Version Date 04/18/24 @ 12:45PM AFLR4 : Compile OS Darwin 23.4.0 x86_64 AFLR4 : Compile Date 04/23/24 @ 11:49AM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.0 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 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 1 1 2 3 6 EGADS : 2 Yes 0 0 1 1 1 1 4 5 EGADS : 3 Yes 0 0 1 1 1 1 4 8 EGADS : 4 Yes 0 0 1 1 1 2 3 5 EGADS : 5 Yes 0 0 1 1 1 2 4 EGADS : 6 Yes 0 0 1 1 1 1 7 8 EGADS : 7 Yes 0 0 1 1 1 6 9 10 EGADS : 8 Yes 0 0 1 1 1 3 6 9 EGADS : 9 Yes 0 0 1 1 1 7 8 10 EGADS : 10 Yes 0 0 1 1 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 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 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 21.7051 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 2651.51 AFLR4 : Abs Min Surf Spacing = 0.0542627 AFLR4 : Min Surf Spacing = 0.108525 AFLR4 : Max Surf Spacing = 2.17051 AFLR4 : Global Scale Factor = 5 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 : 10 CAD geometry 0 STD w/BL AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD 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 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1107 2082 0 AFLR4 : Nodes, Trias,Quads= 685 1238 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1473 2759 0 AFLR4 : Nodes, Trias,Quads= 721 1255 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 1116 2100 0 AFLR4 : Nodes, Trias,Quads= 671 1210 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1458 2729 0 AFLR4 : Nodes, Trias,Quads= 714 1241 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 20 24 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 1108 2084 0 AFLR4 : Nodes, Trias,Quads= 683 1234 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 1488 2789 0 AFLR4 : Nodes, Trias,Quads= 714 1241 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 1112 2092 0 AFLR4 : Nodes, Trias,Quads= 653 1174 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 1456 2725 0 AFLR4 : Nodes, Trias,Quads= 708 1229 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 20 24 0 AFLR4 : Nodes, Trias,Quads= 14 12 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 13 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 14 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 15 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 16 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 4933 9858 1312 AFLR4 : Auto Mode Turned OFF OVERALL : CPU Time = 0.190 seconds Body 1 (of 2) Number of nodes = 4925 Number of elements = 9846 Number of triangle elements = 9846 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 8 Number of elements = 12 Number of triangle elements = 12 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 4933 Total number of elements = 9858 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Getting volume mesh UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.17.15 AFLR2 : Version Date 04/23/24 @ 12:51AM AFLR2 : Compile OS Darwin 23.4.0 x86_64 AFLR2 : Compile Date 04/23/24 @ 11:49AM AFLR2 : Copyright 1994-2021, D.L. Marcum AFLR2 : --------------------------------------- AFLR4 : --------------------------------------- AFLR4 : AFLR4 LIBRARY AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR AFLR4 : Version Number 11.5.14 AFLR4 : Version Date 04/18/24 @ 12:45PM AFLR4 : Compile OS Darwin 23.4.0 x86_64 AFLR4 : Compile Date 04/23/24 @ 11:49AM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.0 EGADS : --------------------------------------- EGADS : EGADS CAD Geometry Setup EGADS : Model has 2 Active Bodies EGADS : Body 0 is a SolidBody EGADS : Body 0 has 1 Shells EGADS : Body 0 has 10 Faces EGADS : Body 0 has 18 Edges EGADS : Body 0 has 10 Loops EGADS : Body 0 has 10 Nodes EGADS : Body 1 is a SolidBody EGADS : Body 1 has 1 Shells EGADS : Body 1 has 6 Faces EGADS : Body 1 has 12 Edges EGADS : Body 1 has 6 Loops EGADS : Body 1 has 8 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 1 1 2 3 6 EGADS : 2 Yes 0 0 1 1 1 1 4 5 EGADS : 3 Yes 0 0 1 1 1 1 4 8 EGADS : 4 Yes 0 0 1 1 1 2 3 5 EGADS : 5 Yes 0 0 1 1 1 2 4 EGADS : 6 Yes 0 0 1 1 1 1 7 8 EGADS : 7 Yes 0 0 1 1 1 6 9 10 EGADS : 8 Yes 0 0 1 1 1 3 6 9 EGADS : 9 Yes 0 0 1 1 1 7 8 10 EGADS : 10 Yes 0 0 1 1 1 7 9 EGADS : 11 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 12 Yes 1 0 1 NA NA 13 14 15 16 EGADS : 13 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 14 Yes 1 0 1 NA NA 11 12 15 16 EGADS : 15 Yes 1 0 1 NA NA 11 12 13 14 EGADS : 16 Yes 1 0 1 NA NA 11 12 13 14 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -5 4 6 -7 EGADS : 3 -3 8 1 -9 EGADS : 4 -6 9 5 -10 EGADS : 5 7 10 EGADS : 6 11 13 -12 -2 EGADS : 7 14 16 -15 -13 EGADS : 8 12 17 -11 -8 EGADS : 9 15 18 -14 -17 EGADS : 10 -16 -18 EGADS : 11 19 20 -21 -22 EGADS : 12 -23 26 25 -24 EGADS : 13 27 23 -28 -19 EGADS : 14 -29 21 30 -25 EGADS : 15 22 29 -26 -27 EGADS : 16 -20 28 24 -30 EGADS : Face Loops Information EGADS : Face Loops EGADS : 1 1 EGADS : 2 2 EGADS : 3 3 EGADS : 4 4 EGADS : 5 5 EGADS : 6 6 EGADS : 7 7 EGADS : 8 8 EGADS : 9 9 EGADS : 10 10 EGADS : 11 11 EGADS : 12 12 EGADS : 13 13 EGADS : 14 14 EGADS : 15 15 EGADS : 16 16 EGADS : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -5 4 6 -7 EGADS : 3 Yes -3 8 1 -9 EGADS : 4 Yes -6 9 5 -10 EGADS : 5 Yes 7 10 EGADS : 6 Yes 11 13 -12 -2 EGADS : 7 Yes 14 16 -15 -13 EGADS : 8 Yes 12 17 -11 -8 EGADS : 9 Yes 15 18 -14 -17 EGADS : 10 Yes -16 -18 EGADS : 11 Yes 19 20 -21 -22 EGADS : 12 Yes -23 26 25 -24 EGADS : 13 Yes 27 23 -28 -19 EGADS : 14 Yes -29 21 30 -25 EGADS : 15 Yes 22 29 -26 -27 EGADS : 16 Yes -20 28 24 -30 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 1 2 1 1 3 EGADS : 2 0 Yes 1 3 1 1 6 EGADS : 3 0 Yes 3 4 1 1 3 EGADS : 4 0 Yes 2 4 1 1 2 EGADS : 5 0 Yes 2 5 1 2 4 EGADS : 6 0 Yes 4 6 1 2 4 EGADS : 7 0 Yes 5 6 1 2 5 EGADS : 8 0 Yes 3 1 1 3 8 EGADS : 9 0 Yes 4 2 1 3 4 EGADS : 10 0 Yes 6 5 1 4 5 EGADS : 11 0 Yes 1 7 1 6 8 EGADS : 12 0 Yes 3 8 1 6 8 EGADS : 13 0 Yes 7 8 1 6 7 EGADS : 14 0 Yes 7 9 1 7 9 EGADS : 15 0 Yes 8 10 1 7 9 EGADS : 16 0 Yes 9 10 1 7 10 EGADS : 17 0 Yes 8 7 1 8 9 EGADS : 18 0 Yes 10 9 1 9 10 EGADS : 19 1 Yes 12 11 NA 11 13 EGADS : 20 1 Yes 11 13 NA 11 16 EGADS : 21 1 Yes 14 13 NA 11 14 EGADS : 22 1 Yes 12 14 NA 11 15 EGADS : 23 1 Yes 16 15 NA 12 13 EGADS : 24 1 Yes 15 17 NA 12 16 EGADS : 25 1 Yes 18 17 NA 12 14 EGADS : 26 1 Yes 16 18 NA 12 15 EGADS : 27 1 Yes 12 16 NA 13 15 EGADS : 28 1 Yes 11 15 NA 13 16 EGADS : 29 1 Yes 14 18 NA 14 15 EGADS : 30 1 Yes 13 17 NA 14 16 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 97.2007855 0 0 EGADS : 2 Yes 97.9335611 0 0 EGADS : 3 Yes 50 0 0 EGADS : 4 Yes 75.3047874 0 0 EGADS : 5 Yes 123.552357 0 4.7180639 EGADS : 6 Yes 118.391317 0 3.99272703 EGADS : 7 Yes 97.9335611 36.1389817 0 EGADS : 8 Yes 75.3047874 36.1389817 0 EGADS : 9 Yes 123.552357 97.6729236 4.7180639 EGADS : 10 Yes 118.391317 97.6729236 3.99272703 EGADS : 11 Yes 0 0 1951.57774 EGADS : 12 Yes 0 0 0 EGADS : 13 Yes 0 1953.45847 1951.57774 EGADS : 14 Yes 0 1953.45847 0 EGADS : 15 Yes 2040.21562 0 1951.57774 EGADS : 16 Yes 2040.21562 0 0 EGADS : 17 Yes 2040.21562 1953.45847 1951.57774 EGADS : 18 Yes 2040.21562 1953.45847 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 3906.92 AFLR4 : Min Bounding Box Length = 3906.92 AFLR4 : Max Ref Bounding Box Length = 195.346 AFLR4 : Min Ref Bounding Box Length = 13.1976 AFLR4 : Reference Length = 13.1976 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 428.309 AFLR4 : Abs Min Surf Spacing = 0.032994 AFLR4 : Min Surf Spacing = 0.065988 AFLR4 : Max Surf Spacing = 1.31976 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 AFLR4 : 2 CAD geometry 0 STD AFLR4 : 3 CAD geometry 0 STD AFLR4 : 4 CAD geometry 0 STD AFLR4 : 5 CAD geometry 0 STD AFLR4 : 6 CAD geometry 0 STD AFLR4 : 7 CAD geometry 0 STD AFLR4 : 8 CAD geometry 0 STD AFLR4 : 9 CAD geometry 0 STD AFLR4 : 10 CAD geometry 0 STD AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 CAD geometry 0 FARFIELD AFLR4 : 13 CAD geometry 0 FARFIELD AFLR4 : 14 CAD geometry 0 FARFIELD AFLR4 : 15 CAD geometry 0 FARFIELD AFLR4 : 16 CAD geometry 0 FARFIELD 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 : Define CAD surface definition 10 AFLR4 : Define CAD surface definition 11 AFLR4 : Define CAD surface definition 12 AFLR4 : Define CAD surface definition 13 AFLR4 : Define CAD surface definition 14 AFLR4 : Define CAD surface definition 15 AFLR4 : Define CAD surface definition 16 AFLR43 : INPUT SURFACE MESH FROM TESS AFLR43 : Quad Surface Faces= 0 AFLR43 : Tria Surface Faces= 9858 AFLR43 : Nodes = 4933 UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR UG PARAM : mrecm = 3 UG PARAM : mrecqm = 3 UG PARAM : mpfrmt = 0 AFLR3 : --------------------------------------- AFLR3 : AFLR3 LIBRARY AFLR3 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR3 : TETRAHEDRAL GRID GENERATOR AFLR3 : Version Number 16.32.50 AFLR3 : Version Date 10/31/23 @ 06:31PM AFLR3 : Compile OS Darwin 22.6.0 x86_64 AFLR3 : Compile Date 11/01/23 @ 12:19PM AFLR3 : Copyright 1994-2021, D.L. Marcum AFLR3 : --------------------------------------- AFLR3 IC : INPUT SURFACE GRID CHECK AFLR3 IC : Nodes, Elements = 4933 0 UG3 : Boundary Conditions UG3 : B-Face ID Boundary Condition UG3 : 1 Solid UG3 : 2 Solid UG3 : 3 Solid UG3 : 4 Solid UG3 : 5 Solid UG3 : 6 Solid UG3 : 7 Solid UG3 : 8 Solid UG3 : 9 Solid UG3 : 10 Solid UG3 : 11 FarField UG3 : 12 FarField UG3 : 13 FarField UG3 : 14 FarField UG3 : 15 FarField UG3 : 16 FarField AFLR3 : CPU Time = 0.020 seconds AFLR3 IG : INITIAL VOLUME GRID GENERATION AFLR3 IG : Nodes, Elements = 4933 0 AFLR3 IG : Nodes, Elements = 8 10 AFLR3 IG : Nodes, Elements = 988 7142 AFLR3 IG : Nodes, Elements = 1976 14311 AFLR3 IG : Nodes, Elements = 2964 22901 AFLR3 IG : Nodes, Elements = 3952 31940 AFLR3 IG : Nodes, Elements = 4940 40111 AFLR3 IG : Nodes, Elements = 4940 40004 AFLR3 IG : Nodes, Elements = 4940 40007 AFLR3 IG : Nodes, Elements = 4940 39931 AFLR3 IG : Nodes, Elements = 4933 25885 AFLR3 IG : Nodes, Elements = 4933 26051 AFLR3 IG : Nodes, Elements = 4933 14490 AFLR3 IG : Nodes, Elements = 4933 13234 AFLR3 : CPU Time = 0.123 seconds AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION AFLR3 GG : Nodes, Elements = 4933 13234 AFLR3 GG : Nodes, Elements = 4987 13396 AFLR3 GG : Nodes, Elements = 4987 13472 AFLR3 GG : Nodes, Elements = 4987 13267 AFLR3 GG : Nodes, Elements = 5017 13357 AFLR3 GG : Nodes, Elements = 5017 13615 AFLR3 GG : Nodes, Elements = 5017 13543 AFLR3 GG : Nodes, Elements = 5078 13727 AFLR3 GG : Nodes, Elements = 5078 13891 AFLR3 GG : Nodes, Elements = 5078 13446 AFLR3 GG : Nodes, Elements = 5165 13707 AFLR3 GG : Nodes, Elements = 5165 14180 AFLR3 GG : Nodes, Elements = 5165 13827 AFLR3 GG : Nodes, Elements = 5224 14004 AFLR3 GG : Nodes, Elements = 5224 14359 AFLR3 GG : Nodes, Elements = 5224 14077 AFLR3 GG : Nodes, Elements = 5268 14209 AFLR3 GG : Nodes, Elements = 5268 14458 AFLR3 GG : Nodes, Elements = 5268 14303 AFLR3 GG : Nodes, Elements = 5300 14399 AFLR3 GG : Nodes, Elements = 5300 14636 AFLR3 GG : Nodes, Elements = 5300 14496 AFLR3 GG : Nodes, Elements = 5321 14559 AFLR3 GG : Nodes, Elements = 5321 14707 AFLR3 GG : Nodes, Elements = 5321 14603 AFLR3 GG : Nodes, Elements = 5336 14648 AFLR3 GG : Nodes, Elements = 5336 14741 AFLR3 GG : Nodes, Elements = 5336 14666 AFLR3 GG : Nodes, Elements = 5344 14690 AFLR3 GG : Nodes, Elements = 5344 14728 AFLR3 GG : Nodes, Elements = 5344 14710 AFLR3 GG : Nodes, Elements = 5348 14722 AFLR3 GG : Nodes, Elements = 5348 14753 AFLR3 GG : Nodes, Elements = 5348 14733 AFLR3 GG : Nodes, Elements = 5350 14739 AFLR3 GG : Nodes, Elements = 5350 14746 AFLR3 GG : Nodes, Elements = 5350 14743 AFLR3 GG : Nodes, Elements = 5353 14752 AFLR3 GG : Nodes, Elements = 5353 14766 AFLR3 GG : Nodes, Elements = 5353 14760 AFLR3 : CPU Time = 0.070 seconds AFLR3 QI : QUALITY IMPROVEMENT AFLR3 QI : Nodes, Elements = 5353 14760 AFLR3 QI : Nodes, Elements = 5305 14479 AFLR3 QI : Nodes, Elements = 5281 14338 AFLR3 QI : Nodes, Elements = 5274 14298 AFLR3 QI : Nodes, Elements = 5273 14292 AFLR3 QI : Nodes, Elements = 5273 19714 AFLR3 QI : Nodes, Elements = 5273 15107 AFLR3 QI : Nodes, Elements = 5273 13825 AFLR3 QI : Nodes, Elements = 5273 19727 AFLR3 QI : Nodes, Elements = 5273 15071 AFLR3 QI : Nodes, Elements = 5273 13896 AFLR3 QI : Nodes, Elements = 5273 19727 AFLR3 QI : Nodes, Elements = 5273 15059 AFLR3 QI : Nodes, Elements = 5273 13749 AFLR3 QI : Nodes, Elements = 5273 19724 AFLR3 QI : Nodes, Elements = 5273 15101 AFLR3 QI : Nodes, Elements = 5273 13821 AFLR3 QI : Nodes, Elements = 5273 19722 AFLR3 QI : Nodes, Elements = 5273 15081 AFLR3 QI : Nodes, Elements = 5273 13905 AFLR3 QI : Nodes, Elements = 5273 13725 AFLR3 QI : Nodes, Elements = 5317 13899 AFLR3 QI : Nodes, Elements = 5317 21044 AFLR3 QI : Nodes, Elements = 5317 14814 AFLR3 QI : Nodes, Elements = 5317 14269 AFLR3 QI : Nodes, Elements = 5317 17679 AFLR3 QI : Nodes, Elements = 5317 14301 AFLR3 QI : Nodes, Elements = 5317 13830 AFLR3 : CPU Time = 0.255 seconds AFLR3 QRG: QUALITY GRID RE-GENERATION AFLR3 QRG: Nodes, Elements = 5317 13830 AFLR3 : CPU Time = 0.005 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 13830 UG3 : Min, Max Ang = 0.006596 179.7 UG3 : Average Angle = 73.4 UG3 : No. Angle>160.0 = 1922 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 13830 UG3 : Min Vol = 0.000293 UG3 : Average Vol = 4.31e+06 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol<TOL = 0 UG3 : Q VOL-LENGTH-RATIO CHECK 2/3 2 UG3 : Q = c * Vol / sum( L ) UG3 : 0 <= Q <= 1 UG3 : No. Tet Elems = 13830 UG3 : Min, Max Q = 1.25e-05 1 UG3 : Average Q = 0.106 UG3 : No. Q< 0.1 = 10496 UG3 : No. Q< 0.01 = 8943 OVERALL : CPU Time = 0.487 seconds UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 13830 UG3 : Min, Max Ang = 0.006596 179.7 UG3 : Average Angle = 73.4 UG3 : No. Angle>160.0 = 1922 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 5.96e+10 UG3 : No. Tet Elems = 13830 UG3 : Min Vol = 0.000293 UG3 : Average Vol = 4.31e+06 UG3 : Total-Tet-Vol = 5.96e+10 UG3 : No. Vol<TOL = 0 UG3 : Q VOL-LENGTH-RATIO CHECK 2/3 2 UG3 : Q = c * Vol / sum( L ) UG3 : 0 <= Q <= 1 UG3 : Note that L includes scaling for BL-aspect=ratio UG3 : No. Tet Elems = 13830 UG3 : Min, Max Q = 0.0034 1 UG3 : Average Q = 0.186 UG3 : No. Q< 0.1 = 8713 UG3 : No. Q< 0.01 = 59 UG3 : CPU Time = 0.000 seconds EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.26 EGADS : OpenCASCADE Version 7.8.0 EGADS : --------------------------------------- EGADS : CREATE EGADS TESS FROM AFLR3 DATA EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 1 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 2 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 3 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 4 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 5 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 6 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 7 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 8 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 9 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 10 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 11 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 12 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 13 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 14 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 15 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 16 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 17 EGADS : CREATING TESSELLATION FOR BODY 0 EDGE 18 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 1 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 2 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 3 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 4 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 5 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 6 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 7 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 8 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 9 EGADS : CREATING TESSELLATION FOR BODY 0 FACE 10 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 19 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 20 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 21 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 22 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 23 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 24 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 25 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 26 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 27 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 28 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 29 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 30 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 11 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 12 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 13 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 14 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 15 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 16 EGADS : EGADS TESS CREATED EGADS : CHECK TESS FACE NODE MAP EGADS : CHECKING NODE MAP FOR BODY 0 FACE 1 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 2 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 3 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 4 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 5 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 6 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 7 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 8 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 9 EGADS : CHECKING NODE MAP FOR BODY 0 FACE 10 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 11 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 12 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 13 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 14 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 15 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 16 Volume mesh: Number of nodes = 5317 Number of elements = 23688 Number of triangles = 9858 Number of quadrilatarals = 0 Number of tetrahedrals = 13830 Number of pyramids = 0 Number of prisms = 0 Number of hexahedrals = 0 Writing SU2 file .... Finished writing SU2 file Getting CFD boundary conditions Boundary condition name - Farfield Boundary condition name - Wing Done getting CFD boundary conditions Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticIterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" ==> Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. 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 4240 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 195.346 m. Reference origin for moment evaluation is (55.4263, 0, 0). Surface(s) where the force coefficients are evaluated: BC_1. Surface(s) plotted in the output file: BC_1. Surface(s) affected by the design variables: BC_1. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat. Surface file name: surface_flow_aeroelasticIterative. Volume file name: flow_aeroelasticIterative. Restart file name: restart_flow_aeroelasticIterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | Far-field| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 5317 grid points. 13830 volume elements. 2 surface markers. 9846 boundary elements in index 0 (Marker = BC_1). 12 boundary elements in index 1 (Marker = BC_2). 13830 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: 5.96352e+10. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 17.3483. Mean K: 1.87862. Standard deviation K: 2.72111. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 2.51936| 87.7801| | CV Face Area Aspect Ratio| 1.28339| 2.80217e+07| | CV Sub-Volume Ratio| 1.04782| 3.92559e+08| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 5317| 1/1.00| 10| | 1| 1307| 1/4.07| 9.39639| | 2| 226| 1/5.78| 7.85229| +-------------------------------------------+ Finding max control volume width. Semi-span length = 97.6729 m. Wetted area = 8234.67 m^2. Area projection in the x-plane = 668.083 m^2, y-plane = 415.155 m^2, z-plane = 3916.84 m^2. Max. coordinate in the x-direction = 123.552 m, y-direction = 97.6729 m, z-direction = 4.71806 m. Min. coordinate in the x-direction = 50 m, y-direction = -97.6729 m, z-direction = -8.4717 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.3214e-01| 1.778264| 4.052124| 3.540124| 7.247370| 0.973936| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.2874e-01| 4.266331| 6.508794| 6.312424| 9.744623| 1.276334| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.2799e-01| 4.694136| 6.868432| 6.719019| 10.169102| 1.712250| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.2781e-01| 4.759562| 7.133453| 7.156909| 10.229087| 2.077370| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.2857e-01| 5.227682| 7.724181| 7.671986| 10.709910| 2.715222| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 5.22768| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticIterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |CSV file |surface_flow_aeroelasticIterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |Tecplot binary |flow_aeroelasticIterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |Tecplot binary surface |surface_flow_aeroelasticIterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). +-----------------------------------------------------------------------+ --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ ==> Running SU2 post-analysis... ==> Running ASTROS pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 2 Name = wingSpar1, index = 1 Name = wingSpar2, index = 2 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 425 Number of elements = 482 Number of triangle elements = 0 Number of quadrilateral elements = 482 ---------------------------- Total number of nodes = 425 Total number of elements = 482 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 4 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Name = leftPointLoad, index = 3 Name = ritePointLoad, index = 4 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 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 = 5 Name = leftWingSkin, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = wingSpar2, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 425 Number of elements = 482 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 482 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, 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_aeroelasticIterative.csv Number of variables = 16 Number of data points = 4925 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure' Rank 0: src = 2.672164e+12, tgt = 2.672164e+12, diff = 1.047939e+03 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 4925 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure' Rank 0: src = 2.593437e+12, tgt = 2.593437e+12, diff = 8.613745e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 4925 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure' Rank 0: src = 8.633345e+08, tgt = 8.633344e+08, diff = 7.283864e+01 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 4925 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure' Rank 0: src = 8.635510e+08, tgt = 8.635511e+08, diff = 1.545147e+02 Extracting external pressure loads from data transfer.... TransferName = upperWing Number of Elements = 98 (total = 98) Extracting external pressure loads from data transfer.... TransferName = lowerWing Number of Elements = 98 (total = 196) Extracting external pressure loads from data transfer.... TransferName = leftTip Number of Elements = 17 (total = 213) Extracting external pressure loads from data transfer.... TransferName = riteTip Number of Elements = 17 (total = 230) 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 Writing coordinate system cards ==> Running mASTROS...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running ASTROS post-analysis... ==> Running SU2 pre-analysis... Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 1 Done boundary flags Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticIterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "Harrier (8.0.1)" ==> Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (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_CAPS.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_CAPS.su2. Cell stiffness scaled by distance to nearest solid surface. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | Far-field| BC_2| +-----------------------------------------------------------------------+ Three dimensional problem. 5317 grid points. 13830 volume elements. 2 surface markers. 9846 boundary elements in index 0 (Marker = BC_1). 12 boundary elements in index 1 (Marker = BC_2). 13830 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: 5.96352e+10. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive. Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. --------------------- Surface grid deformation (ZONE 0) ----------------- Performing the deformation of the surface grid. Updating the surface coordinates from the input file. ------------------- Volumetric grid deformation (ZONE 0) ---------------- Performing the deformation of the volumetric grid. WARNING: Convexity is not checked for 3D elements (issue #1171). Completed in 0.266916 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_CAPS.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 4240 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 195.346 m. Reference origin for moment evaluation is (55.4263, 0, 0). Surface(s) where the force coefficients are evaluated: BC_1. Surface(s) plotted in the output file: BC_1. Surface(s) affected by the design variables: BC_1. Input mesh file name: ../aflr3/aflr3_CAPS.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat. Surface file name: surface_flow_aeroelasticIterative. Volume file name: flow_aeroelasticIterative. Restart file name: restart_flow_aeroelasticIterative.dat. ------------- Config File Boundary Information ( Zone 0 ) --------------- +-----------------------------------------------------------------------+ | Marker Type| Marker Name| +-----------------------------------------------------------------------+ | Euler wall| BC_1| +-----------------------------------------------------------------------+ | Far-field| BC_2| +-----------------------------------------------------------------------+ -------------------- Output Preprocessing ( Zone 0 ) -------------------- WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...) Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF Convergence field(s): RMS_DENSITY Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive. Volume output fields: COORDINATES, SOLUTION, PRIMITIVE ------------------- Geometry Preprocessing ( Zone 0 ) ------------------- Three dimensional problem. 5317 grid points. 13830 volume elements. 2 surface markers. 9846 boundary elements in index 0 (Marker = BC_1). 12 boundary elements in index 1 (Marker = BC_2). 13830 tetrahedra. Setting point connectivity. Renumbering points (Reverse Cuthill McKee Ordering). Recomputing point connectivity. Setting element connectivity. Checking the numerical grid orientation. There has been a re-orientation of 5917 TETRAHEDRON volume elements. There has been a re-orientation of 4468 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 6.00342e+10. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 37.3071. Mean K: 1.74078. Standard deviation K: 2.28541. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.516955| 78.9368| | CV Face Area Aspect Ratio| 1.30468| 5.8651e+06| | CV Sub-Volume Ratio| 1.08274| 8.83199e+09| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 5317| 1/1.00| 10| | 1| 1323| 1/4.02| 9.43457| | 2| 220| 1/6.01| 7.78218| +-------------------------------------------+ Finding max control volume width. Semi-span length = 122.669 m. Wetted area = 632464 m^2. Area projection in the x-plane = 294887 m^2, y-plane = 82010.6 m^2, z-plane = 33419.1 m^2. Max. coordinate in the x-direction = 167.237 m, y-direction = 122.669 m, z-direction = 271.513 m. Min. coordinate in the x-direction = 44.3948 m, y-direction = -125.872 m, z-direction = -460.969 m. Checking if Euler & Symmetry markers are straight/plane: Boundary marker BC_1 is NOT a single plane. Computing wall distances. -------------------- Solver Preprocessing ( Zone 0 ) -------------------- Inviscid flow: Computing density based on free-stream temperature and pressure using the ideal gas law. Force coefficients computed using free-stream values. -- Models: +------------------------------------------------------------------------------+ | Viscosity Model| Conductivity Model| Fluid Model| +------------------------------------------------------------------------------+ | -| -| STANDARD_AIR| +------------------------------------------------------------------------------+ -- Fluid properties: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Gas Constant| 287.058| 1| N.m/kg.K| 287.058| | Spec. Heat Ratio| -| -| -| 1.4| +------------------------------------------------------------------------------+ -- Initial and free-stream conditions: +------------------------------------------------------------------------------+ | Name| Dim. value| Ref. value| Unit|Non-dim. value| +------------------------------------------------------------------------------+ | Static Pressure| 101325| 1| Pa| 101325| | Density| 1.22498| 1| kg/m^3| 1.22498| | Temperature| 288.15| 1| K| 288.15| | Total Energy| 211798| 1| m^2/s^2| 211798| | Velocity-X| 100.087| 1| m/s| 100.087| | Velocity-Y| 0| 1| m/s| 0| | Velocity-Z| 0| 1| m/s| 0| | Velocity Magnitude| 100.087| 1| m/s| 100.087| +------------------------------------------------------------------------------+ | Mach Number| -| -| -| 0.294118| +------------------------------------------------------------------------------+ Initialize Jacobian structure (Euler). MG level: 0. Initialize Jacobian structure (Euler). MG level: 1. Initialize Jacobian structure (Euler). MG level: 2. ------------------- Numerics Preprocessing ( Zone 0 ) ------------------- ----------------- Integration Preprocessing ( Zone 0 ) ------------------ ------------------- Iteration Preprocessing ( Zone 0 ) ------------------ Euler/Navier-Stokes/RANS fluid iteration. ------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better, see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations +----------------------------------------------------------------------------------------------------------------------------------------------+ | Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff| +----------------------------------------------------------------------------------------------------------------------------------------------+ | 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.2271e-01| 6.555381| 9.522203| 9.454807| 12.024487| -0.098630| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.2049e-01| 7.262741| 9.654694| 9.723569| 12.765172| 0.076010| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.1864e-01| 7.170902| 9.794731| 9.769565| 12.690244| 0.272611| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.1832e-01| 7.735267| 10.094799| 10.177076| 13.152018| 0.910745| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.1771e-01| 7.315544| 9.967883| 9.850940| 13.042115| -0.902591| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 7.31554| < -14| No| +-----------------------------------------------------------------------+ ------------------------------------------------------------------------- +-----------------------------------------------------------------------+ | File Writing Summary | Filename | +-----------------------------------------------------------------------+ |SU2 binary restart |restart_flow_aeroelasticIterative.dat| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |CSV file |surface_flow_aeroelasticIterative.csv| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |Tecplot binary |flow_aeroelasticIterative.szplt | Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). |Tecplot binary surface |surface_flow_aeroelasticIterative.szplt| Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat). +-----------------------------------------------------------------------+ Warning: there are 1067 non-physical points in the solution. Warning: 565 reconstructed states for upwinding are non-physical. --------------------------- Finalizing Solver --------------------------- Deleted CNumerics container. Deleted CIntegration container. Deleted CSolver container. Deleted CIteration container. Deleted CInterface container. Deleted CGeometry container. Deleted CFreeFormDefBox class. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted nInst container. Deleted COutput class. ------------------------------------------------------------------------- ------------------------- Exit Success (SU2_CFD) ------------------------ ==> Running SU2 post-analysis... ==> Running ASTROS pre-analysis... Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 4925 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure' Rank 0: src = 1.566709e+12, tgt = 1.566709e+12, diff = 3.276406e+02 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 4925 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure' Rank 0: src = 1.382698e+12, tgt = 1.382698e+12, diff = 1.450830e+01 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 4925 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure' Rank 0: src = 4.329146e+08, tgt = 4.329146e+08, diff = 3.918651e+01 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 4925 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure' Rank 0: src = 8.274979e+08, tgt = 8.274982e+08, diff = 3.115343e+02 Extracting external pressure loads from data transfer.... TransferName = upperWing Number of Elements = 98 (total = 98) Extracting external pressure loads from data transfer.... TransferName = lowerWing Number of Elements = 98 (total = 196) Extracting external pressure loads from data transfer.... TransferName = leftTip Number of Elements = 17 (total = 213) Extracting external pressure loads from data transfer.... TransferName = riteTip Number of Elements = 17 (total = 230) 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 Writing coordinate system cards ==> Running mASTROS...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running ASTROS post-analysis... real 0m48.320s user 1m3.271s sys 0m25.808s + status=0 + set +x ================================================= data/session10/2_aeroelastic_Iterative_SU2_Astros.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Did not run examples for: session08 fun3d session10 nastran session11 fun3d+astros ================================================= ================================================= Summary of examples NOT finished as expected data/session04/5_mses_OpenMDAO_CD_camber.py data/session04/7_mses_OpenMDAO_CL2_camber.py data/session04/8_mses_OpenMDAO_CDCL.py data/session09/6_tacs_StaticCantilever.py.py See training.log for more details. ================================================= ================================================= ================================================= Build step 'Execute shell' marked build as failure [GNU C Compiler (gcc)Clang] Skipping execution of recorder since overall result is 'FAILURE' [PostBuildScript] - [INFO] Executing post build scripts. [PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX [WS-CLEANUP] Deleting project workspace... [WS-CLEANUP] Skipped based on build state FAILURE Finished: FAILURE