The Jenkins Controller is preparing for shutdown. No new builds can be started.
Skipping 2,258 KB.. Full LogUsing a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | PARAVIEW| 250| | SURFACE_PARAVIEW| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_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. 5410 grid points. 14506 volume elements. 2 surface markers. 9846 boundary elements in index 0 (Marker = BC_1). 12 boundary elements in index 1 (Marker = BC_2). 14506 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: 1.87804. Standard deviation K: 2.71985. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.0356459| 84.8625| | CV Face Area Aspect Ratio| 1.15159| 1.8064e+08| | CV Sub-Volume Ratio| 1.04183| 1.2433e+11| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 5410| 1/1.00| 10| | 1| 1326| 1/4.08| 9.38729| | 2| 295| 1/4.49| 8.53213| +-------------------------------------------+ Finding max control volume width. Semi-span length = 97.6729 m. Wetted area = 8224.75 m^2. Area projection in the x-plane = 667.964 m^2, y-plane = 414.363 m^2, z-plane = 3909.94 m^2. Max. coordinate in the x-direction = 127.552 m, y-direction = 97.6729 m, z-direction = 7.71806 m. Min. coordinate in the x-direction = 54 m, y-direction = -97.6729 m, z-direction = -5.4717 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| 1.5683e-01| 2.019590| 4.394767| 3.778108| 7.502435| 1.411376| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.5535e-01| 4.302110| 6.853009| 6.913878| 9.811799| 1.299087| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.5450e-01| 4.699192| 7.326483| 7.468524| 10.213388| 1.194594| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.5417e-01| 4.939499| 7.330289| 7.676458| 10.438226| 1.136373| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.5373e-01| 5.207258| 7.567472| 7.904306| 10.695804| 1.129595| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 5.20726| < -14| 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 = 0.080618 Cd = 0.071369 --> Cmx = 0.000213 Cmy = -0.022739 Cmz = 0.000187 --> Cx = 0.069951 Cy = 0.00055 Cz = 0.081851 real 0m3.708s user 0m3.350s sys 0m0.699s + status=0 + set +x ================================================= data/session08/su2_1_InviscidWing.py passed (as expected) ================================================= ================================================= tess_1_Geom.py test; + python tess_1_Geom.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory real 0m12.933s user 0m21.059s sys 2m10.426s + status=0 + set +x ================================================= data/session09/tess_1_Geom.py passed (as expected) ================================================= ================================================= tess_2_TFI_Templates.py test; + python tess_2_TFI_Templates.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 11092 Number of elements = 22807 Number of triangle elements = 22807 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11092 Total number of elements = 22807 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 11921 Number of elements = 24465 Number of triangle elements = 24465 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11921 Total number of elements = 24465 real 0m12.214s user 0m22.107s sys 2m7.789s + status=0 + set +x ================================================= data/session09/tess_2_TFI_Templates.py passed (as expected) ================================================= ================================================= tess_3_Params.py test; + python tess_3_Params.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 732 Number of elements = 1781 Number of triangle elements = 1781 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 732 Total number of elements = 1781 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 934 Number of elements = 2228 Number of triangle elements = 2228 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 934 Total number of elements = 2228 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 3545 Number of elements = 7669 Number of triangle elements = 7669 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3545 Total number of elements = 7669 real 0m12.429s user 0m22.348s sys 2m11.752s + status=0 + set +x ================================================= data/session09/tess_3_Params.py passed (as expected) ================================================= ================================================= tess_4_Params.py test; + python tess_4_Params.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 1406 Number of elements = 3137 Number of triangle elements = 3137 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 1406 Total number of elements = 3137 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 2097 Number of elements = 4570 Number of triangle elements = 4570 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 2097 Total number of elements = 4570 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 6562 Number of elements = 13689 Number of triangle elements = 13689 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 6562 Total number of elements = 13689 real 0m12.010s user 0m22.085s sys 2m1.442s + status=0 + set +x ================================================= data/session09/tess_4_Params.py passed (as expected) ================================================= ================================================= tess_5_Params.py test; + python tess_5_Params.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 3537 Number of elements = 7415 Number of triangle elements = 7415 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3537 Total number of elements = 7415 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 12458 Number of elements = 25384 Number of triangle elements = 25384 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 12458 Total number of elements = 25384 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 45075 Number of elements = 90817 Number of triangle elements = 90817 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 45075 Total number of elements = 90817 real 0m14.562s user 0m29.733s sys 2m8.588s + status=0 + set +x ================================================= data/session09/tess_5_Params.py passed (as expected) ================================================= ================================================= tess_6_TriQuad.py test; + python tess_6_TriQuad.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 8302 Number of elements = 17191 Number of triangle elements = 17191 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 8302 Total number of elements = 17191 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 72029 Number of elements = 74322 Number of triangle elements = 0 Number of quadrilateral elements = 74322 ---------------------------- Total number of nodes = 72029 Total number of elements = 74322 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 1655 Number of elements = 3225 Number of triangle elements = 3225 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 1655 Total number of elements = 3225 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 3009 Number of elements = 2928 Number of triangle elements = 0 Number of quadrilateral elements = 2928 ---------------------------- Total number of nodes = 3009 Total number of elements = 2928 real 0m18.463s user 0m27.603s sys 2m0.443s + status=0 + set +x ================================================= data/session09/tess_6_TriQuad.py passed (as expected) ================================================= ================================================= tess_7_MeshSizing.py test; + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log + python tess_7_MeshSizing.py ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 8302 Number of elements = 17191 Number of triangle elements = 17191 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 8302 Total number of elements = 17191 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - leadingEdge Mesh sizing name - rootLeadingEdge Done getting mesh sizing parameters Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 3919 Number of elements = 8410 Number of triangle elements = 8410 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3919 Total number of elements = 8410 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - leadingEdge Mesh sizing name - rootLeadingEdge Done getting mesh sizing parameters Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 6181 Number of elements = 6607 Number of triangle elements = 0 Number of quadrilateral elements = 6607 ---------------------------- Total number of nodes = 6181 Total number of elements = 6607 real 0m11.907s user 0m20.627s sys 1m15.166s + status=0 + set +x ================================================= data/session09/tess_7_MeshSizing.py passed (as expected) ================================================= ================================================= tess_8_MeshSizing.py test; + python tess_8_MeshSizing.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 1655 Number of elements = 3225 Number of triangle elements = 3225 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 1655 Total number of elements = 3225 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting mesh sizing parameters Mesh sizing name - rootLeadingEdge Mesh sizing name - wingSpar1 Done getting mesh sizing parameters Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 6587 Number of elements = 13200 Number of triangle elements = 13200 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 6587 Total number of elements = 13200 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting mesh sizing parameters Mesh sizing name - rootLeadingEdge Mesh sizing name - wingSpar1 Done getting mesh sizing parameters Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 22190 Number of elements = 22191 Number of triangle elements = 0 Number of quadrilateral elements = 22191 ---------------------------- Total number of nodes = 22190 Total number of elements = 22191 real 0m13.666s user 0m21.692s sys 1m17.728s + status=0 + set +x ================================================= data/session09/tess_8_MeshSizing.py passed (as expected) ================================================= ================================================= tess_MinQuad.py test; + python tess_MinQuad.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../../data/ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 299 Number of elements = 387 Number of triangle elements = 0 Number of quadrilateral elements = 387 ---------------------------- Total number of nodes = 299 Total number of elements = 387 --> Total Elements 387 real 0m11.198s user 0m17.484s sys 1m29.715s + status=0 + set +x ================================================= solutions/session09/tess_MinQuad.py passed (as expected) ================================================= ================================================= tess_2k.py test; + python tess_2k.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../../data/ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting mesh sizing parameters Mesh sizing name - rootLeadingEdge Done getting mesh sizing parameters Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 1289 Number of elements = 1189 Number of triangle elements = 0 Number of quadrilateral elements = 1189 ---------------------------- Total number of nodes = 1289 Total number of elements = 1189 --> Total Elements 1189 real 0m11.576s user 0m17.150s sys 1m20.920s + status=0 + set +x ================================================= solutions/session09/tess_2k.py passed (as expected) ================================================= ================================================= astros_1_ModalClamped.py test; + python astros_1_ModalClamped.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running ASTROS pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 235 Number of elements = 227 Number of triangle elements = 0 Number of quadrilateral elements = 227 ---------------------------- Total number of nodes = 235 Total number of elements = 227 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 = 2 Name = ritePointLoad, index = 1 Name = leftPointLoad, 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 = 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 = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 235 Number of elements = 227 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 227 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... 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 : 0.0357647 2 : 0.102451 3 : 0.102451 4 : 0.159637 5 : 0.159637 6 : 0.215446 7 : 0.215446 8 : 0.350115 9 : 0.350115 10: 0.466966 real 0m13.159s user 0m20.015s sys 1m21.927s + status=0 + set +x ================================================= data/session10/astros_1_ModalClamped.py passed (as expected) ================================================= ================================================= astros_2_ModalSupport.py test; + python astros_2_ModalSupport.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running ASTROS pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Name = ribSupport, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting surface mesh for body 1 (of 2) Getting surface mesh for body 2 (of 2) Body 1 (of 2) Number of nodes = 235 Number of elements = 227 Number of triangle elements = 0 Number of quadrilateral elements = 227 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 = 236 Total number of elements = 227 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 = ritePointLoad, index = 1 Name = leftPointLoad, 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 = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Name = ribSupport, index = 6 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 235 Number of elements = 227 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 227 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 = 236 Combined Number of elements = 228 Combined Elemental Nodes = 1 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 227 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 19 automatic connections were made for capsConnect ribRoot (node id 236) 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... 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 : 0.0 2 : 0.0357647 3 : 0.0365801 4 : 0.102451 5 : 0.102453 6 : 0.159637 7 : 0.1611 8 : 0.215446 9 : 0.215462 10: 0.350115 real 0m13.530s user 0m20.908s sys 1m23.747s + status=0 + set +x ================================================= data/session10/astros_2_ModalSupport.py passed (as expected) ================================================= ================================================= astros_3_StaticClamped.py test; + python astros_3_StaticClamped.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running ASTROS pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 235 Number of elements = 227 Number of triangle elements = 0 Number of quadrilateral elements = 227 ---------------------------- Total number of nodes = 235 Total number of elements = 227 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 = 2 Name = ritePointLoad, index = 1 Name = leftPointLoad, 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 = 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 = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 235 Number of elements = 227 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 227 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... --> Maximum displacements: --> Tmax 43461.879162311016 --> T1max 738.595 --> T2max 3686.25 --> T3max 43363.8 real 0m13.080s user 0m20.549s sys 2m2.835s + status=0 + set +x ================================================= data/session10/astros_3_StaticClamped.py passed (as expected) ================================================= ================================================= astros_4_Composite.py test; + python astros_4_Composite.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running ASTROS pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 235 Number of elements = 227 Number of triangle elements = 0 Number of quadrilateral elements = 227 ---------------------------- Total number of nodes = 235 Total number of elements = 227 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 = 2 Name = ritePointLoad, index = 1 Name = leftPointLoad, 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 = 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 = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 235 Number of elements = 227 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 227 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... --> Maximum displacements: --> Tmax 12131.654370141774 --> T1max 275.241 --> T2max 1005.74 --> T3max 12103.5 real 0m13.513s user 0m21.003s sys 1m56.543s + status=0 + set +x ================================================= data/session10/astros_4_Composite.py passed (as expected) ================================================= ================================================= nastran_5_Flutter.py test; + python nastran_5_Flutter.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running Nastran pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = Wing, index = 1 Name = wingSpar2, index = 2 Name = wingRib, index = 3 Name = riteWingSkin, index = 4 Name = wingSpar1, index = 5 Name = leftWingSkin, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 4) Getting surface mesh for body 2 (of 4) Getting surface mesh for body 3 (of 4) Getting surface mesh for body 4 (of 4) Body 1 (of 4) Number of nodes = 11 Number of elements = 6 Number of triangle elements = 0 Number of quadrilateral elements = 6 Body 2 (of 4) Number of nodes = 11 Number of elements = 6 Number of triangle elements = 0 Number of quadrilateral elements = 6 Body 3 (of 4) Number of nodes = 11 Number of elements = 6 Number of triangle elements = 0 Number of quadrilateral elements = 6 Body 4 (of 4) Number of nodes = 939 Number of elements = 1094 Number of triangle elements = 0 Number of quadrilateral elements = 1094 ---------------------------- Total number of nodes = 972 Total number of elements = 1112 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 = 2 Name = ritePointLoad, index = 1 Name = leftPointLoad, 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 = 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 = 6 Name = Wing, index = 1 Name = wingSpar2, index = 2 Name = wingRib, index = 3 Name = riteWingSkin, index = 4 Name = wingSpar1, index = 5 Name = leftWingSkin, index = 6 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 11 Number of elements = 6 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 6 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 11 Number of elements = 6 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 6 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 11 Number of elements = 6 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 6 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 939 Number of elements = 1094 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 1094 Combining multiple FEA meshes! Combined Number of nodal coordinates = 972 Combined Number of elements = 1112 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 1112 Getting vortex lattice surface data VLM surface name - upperWing Done getting vortex lattice surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 108 Surface 2: Number of points found for aero-spline = 108 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 Design_Variable tuple is NULL - No design variables applied 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 Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Flutter 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 mass increment set Writing Nastran instruction file.... Warning: No loads specified for case Flutter!!!! Writing mass increment cards Writing aero card Writing analysis cards, 0 Writing constraint ADD cards Writing constraint cards Writing material cards Writing property cards Writing coordinate system cards Writing aeroelastic cards Done writing aeroelastic cards Done writing files ==> Running Nastran... sh: 1: nastran: not found Traceback (most recent call last): File "/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/data/session10/nastran_5_Flutter.py", line 138, in <module> nastran.postAnalysis() File "/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/problem.py", line 2159, in postAnalysis self._analysisObj.postAnalysis() File "/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed return func(*args, **kwargs) ^^^^^^^^^^^^^^^^^^^^^ File "/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 2914, in postAnalysis if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs)) ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^ File "/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus raise CAPSError(status, msg=msg, errors=errors) pyCAPS.caps.CAPSError: CAPS_IOERR: ================================================================================ nastranAIM.c:3037 in aimPostAnalysis(): Error: Unable to open file: nastran_modal.f06 ================================================================================ real 0m12.385s user 0m20.228s sys 2m9.135s + status=1 + set +x ================================================= data/session10/nastran_5_Flutter.py failed (as NOT expected) ================================================= ================================================= aeroelastic_2_Iterative_SU2_Astros.py test; + python aeroelastic_2_Iterative_SU2_Astros.py + tee -a /jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR2 : Compile Date 04/23/24 @ 12:17PM 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR4 : Compile Date 04/23/24 @ 12:17PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 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 6 Faces EGADS : Body 0 has 10 Edges EGADS : Body 0 has 6 Loops EGADS : Body 0 has 6 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 4 EGADS : 2 Yes 0 0 1 1 1 1 3 5 EGADS : 3 Yes 0 0 1 1 1 1 2 EGADS : 4 Yes 0 0 1 1 1 1 5 6 EGADS : 5 Yes 0 0 1 1 1 2 4 6 EGADS : 6 Yes 0 0 1 1 1 4 5 EGADS : 7 Yes 1 0 1 NA NA 9 10 11 12 EGADS : 8 Yes 1 0 1 NA NA 9 10 11 12 EGADS : 9 Yes 1 0 1 NA NA 7 8 11 12 EGADS : 10 Yes 1 0 1 NA NA 7 8 11 12 EGADS : 11 Yes 1 0 1 NA NA 7 8 9 10 EGADS : 12 Yes 1 0 1 NA NA 7 8 9 10 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -3 5 1 -6 EGADS : 3 4 6 EGADS : 4 7 9 -8 -2 EGADS : 5 8 10 -7 -5 EGADS : 6 -9 -10 EGADS : 7 11 12 -13 -14 EGADS : 8 -15 18 17 -16 EGADS : 9 19 15 -20 -11 EGADS : 10 -21 13 22 -17 EGADS : 11 14 21 -18 -19 EGADS : 12 -12 20 16 -22 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 : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -3 5 1 -6 EGADS : 3 Yes 4 6 EGADS : 4 Yes 7 9 -8 -2 EGADS : 5 Yes 8 10 -7 -5 EGADS : 6 Yes -9 -10 EGADS : 7 Yes 11 12 -13 -14 EGADS : 8 Yes -15 18 17 -16 EGADS : 9 Yes 19 15 -20 -11 EGADS : 10 Yes -21 13 22 -17 EGADS : 11 Yes 14 21 -18 -19 EGADS : 12 Yes -12 20 16 -22 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 2 EGADS : 2 0 Yes 1 3 1 1 4 EGADS : 3 0 Yes 3 4 1 1 2 EGADS : 4 0 Yes 2 4 1 1 3 EGADS : 5 0 Yes 3 1 1 2 5 EGADS : 6 0 Yes 4 2 1 2 3 EGADS : 7 0 Yes 1 5 1 4 5 EGADS : 8 0 Yes 3 6 1 4 5 EGADS : 9 0 Yes 5 6 1 4 6 EGADS : 10 0 Yes 6 5 1 5 6 EGADS : 11 1 Yes 8 7 NA 7 9 EGADS : 12 1 Yes 7 9 NA 7 12 EGADS : 13 1 Yes 10 9 NA 7 10 EGADS : 14 1 Yes 8 10 NA 7 11 EGADS : 15 1 Yes 12 11 NA 8 9 EGADS : 16 1 Yes 11 13 NA 8 12 EGADS : 17 1 Yes 14 13 NA 8 10 EGADS : 18 1 Yes 12 14 NA 8 11 EGADS : 19 1 Yes 8 12 NA 9 11 EGADS : 20 1 Yes 7 11 NA 9 12 EGADS : 21 1 Yes 10 14 NA 10 11 EGADS : 22 1 Yes 9 13 NA 10 12 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 1.61374306 0 0 EGADS : 2 Yes 2.37421202 0 0.355213563 EGADS : 3 Yes 0 0 0 EGADS : 4 Yes 1.40965066 0 0.270825378 EGADS : 5 Yes 2.37421202 3.87298335 0.355213563 EGADS : 6 Yes 1.40965066 3.87298335 0.270825378 EGADS : 7 Yes 0 0 77.6430368 EGADS : 8 Yes 0 0 0 EGADS : 9 Yes 0 77.4596689 77.6430368 EGADS : 10 Yes 0 77.4596689 0 EGADS : 11 Yes 78.6462641 0 77.6430368 EGADS : 12 Yes 78.6462641 0 0 EGADS : 13 Yes 78.6462641 77.4596689 77.6430368 EGADS : 14 Yes 78.6462641 77.4596689 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 154.919 AFLR4 : Min Bounding Box Length = 154.919 AFLR4 : Max Ref Bounding Box Length = 7.74597 AFLR4 : Min Ref Bounding Box Length = 0.433058 AFLR4 : Reference Length = 1.29099 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 105.147 AFLR4 : Abs Min Surf Spacing = 0.00322749 AFLR4 : Min Surf Spacing = 0.00645497 AFLR4 : Max Surf Spacing = 0.129099 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 FARFIELD AFLR4 : 8 CAD geometry 0 FARFIELD AFLR4 : 9 CAD geometry 0 FARFIELD AFLR4 : 10 CAD geometry 0 FARFIELD AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 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 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 1520 2861 0 AFLR4 : Nodes, Trias,Quads= 939 1699 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1511 2844 0 AFLR4 : Nodes, Trias,Quads= 900 1622 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 46 62 0 AFLR4 : Nodes, Trias,Quads= 40 50 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1528 2877 0 AFLR4 : Nodes, Trias,Quads= 929 1679 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 1511 2844 0 AFLR4 : Nodes, Trias,Quads= 895 1612 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 46 62 0 AFLR4 : Nodes, Trias,Quads= 40 50 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 5 4 0 AFLR4 : Nodes, Trias,Quads= 4 2 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 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 3366 6724 786 AFLR4 : Auto Mode Turned OFF OVERALL : CPU Time = 0.115 seconds Body 1 (of 2) Number of nodes = 3358 Number of elements = 6712 Number of triangle elements = 6712 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 = 3366 Total number of elements = 6724 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR2 : Compile Date 04/23/24 @ 12:17PM 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR4 : Compile Date 04/23/24 @ 12:17PM AFLR4 : Copyright 1994-2021, D.L. Marcum AFLR4 : --------------------------------------- EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 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 6 Faces EGADS : Body 0 has 10 Edges EGADS : Body 0 has 6 Loops EGADS : Body 0 has 6 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 4 EGADS : 2 Yes 0 0 1 1 1 1 3 5 EGADS : 3 Yes 0 0 1 1 1 1 2 EGADS : 4 Yes 0 0 1 1 1 1 5 6 EGADS : 5 Yes 0 0 1 1 1 2 4 6 EGADS : 6 Yes 0 0 1 1 1 4 5 EGADS : 7 Yes 1 0 1 NA NA 9 10 11 12 EGADS : 8 Yes 1 0 1 NA NA 9 10 11 12 EGADS : 9 Yes 1 0 1 NA NA 7 8 11 12 EGADS : 10 Yes 1 0 1 NA NA 7 8 11 12 EGADS : 11 Yes 1 0 1 NA NA 7 8 9 10 EGADS : 12 Yes 1 0 1 NA NA 7 8 9 10 EGADS : Face Edges Information EGADS : Face Edges EGADS : 1 -1 2 3 -4 EGADS : 2 -3 5 1 -6 EGADS : 3 4 6 EGADS : 4 7 9 -8 -2 EGADS : 5 8 10 -7 -5 EGADS : 6 -9 -10 EGADS : 7 11 12 -13 -14 EGADS : 8 -15 18 17 -16 EGADS : 9 19 15 -20 -11 EGADS : 10 -21 13 22 -17 EGADS : 11 14 21 -18 -19 EGADS : 12 -12 20 16 -22 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 : Loop Edges Information EGADS : Loop Active Edges EGADS : 1 Yes -1 2 3 -4 EGADS : 2 Yes -3 5 1 -6 EGADS : 3 Yes 4 6 EGADS : 4 Yes 7 9 -8 -2 EGADS : 5 Yes 8 10 -7 -5 EGADS : 6 Yes -9 -10 EGADS : 7 Yes 11 12 -13 -14 EGADS : 8 Yes -15 18 17 -16 EGADS : 9 Yes 19 15 -20 -11 EGADS : 10 Yes -21 13 22 -17 EGADS : 11 Yes 14 21 -18 -19 EGADS : 12 Yes -12 20 16 -22 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 2 EGADS : 2 0 Yes 1 3 1 1 4 EGADS : 3 0 Yes 3 4 1 1 2 EGADS : 4 0 Yes 2 4 1 1 3 EGADS : 5 0 Yes 3 1 1 2 5 EGADS : 6 0 Yes 4 2 1 2 3 EGADS : 7 0 Yes 1 5 1 4 5 EGADS : 8 0 Yes 3 6 1 4 5 EGADS : 9 0 Yes 5 6 1 4 6 EGADS : 10 0 Yes 6 5 1 5 6 EGADS : 11 1 Yes 8 7 NA 7 9 EGADS : 12 1 Yes 7 9 NA 7 12 EGADS : 13 1 Yes 10 9 NA 7 10 EGADS : 14 1 Yes 8 10 NA 7 11 EGADS : 15 1 Yes 12 11 NA 8 9 EGADS : 16 1 Yes 11 13 NA 8 12 EGADS : 17 1 Yes 14 13 NA 8 10 EGADS : 18 1 Yes 12 14 NA 8 11 EGADS : 19 1 Yes 8 12 NA 9 11 EGADS : 20 1 Yes 7 11 NA 9 12 EGADS : 21 1 Yes 10 14 NA 10 11 EGADS : 22 1 Yes 9 13 NA 10 12 EGADS : Node Information EGADS : Node Active Coordinates EGADS : 1 Yes 1.61374306 0 0 EGADS : 2 Yes 2.37421202 0 0.355213563 EGADS : 3 Yes 0 0 0 EGADS : 4 Yes 1.40965066 0 0.270825378 EGADS : 5 Yes 2.37421202 3.87298335 0.355213563 EGADS : 6 Yes 1.40965066 3.87298335 0.270825378 EGADS : 7 Yes 0 0 77.6430368 EGADS : 8 Yes 0 0 0 EGADS : 9 Yes 0 77.4596689 77.6430368 EGADS : 10 Yes 0 77.4596689 0 EGADS : 11 Yes 78.6462641 0 77.6430368 EGADS : 12 Yes 78.6462641 0 0 EGADS : 13 Yes 78.6462641 77.4596689 77.6430368 EGADS : 14 Yes 78.6462641 77.4596689 0 EGADS : Face and Edge Match Information EGADS : No Face Matches Found AFLR4 : Surface Mesh Spacing Setup AFLR4 : Max Bounding Box Length = 154.919 AFLR4 : Min Bounding Box Length = 154.919 AFLR4 : Max Ref Bounding Box Length = 7.74597 AFLR4 : Min Ref Bounding Box Length = 0.433058 AFLR4 : Reference Length = 0.433058 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 16.9832 AFLR4 : Abs Min Surf Spacing = 0.00108265 AFLR4 : Min Surf Spacing = 0.00216529 AFLR4 : Max Surf Spacing = 0.0433058 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 FARFIELD AFLR4 : 8 CAD geometry 0 FARFIELD AFLR4 : 9 CAD geometry 0 FARFIELD AFLR4 : 10 CAD geometry 0 FARFIELD AFLR4 : 11 CAD geometry 0 FARFIELD AFLR4 : 12 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 AFLR43 : INPUT SURFACE MESH FROM TESS AFLR43 : Quad Surface Faces= 0 AFLR43 : Tria Surface Faces= 6724 AFLR43 : Nodes = 3366 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR3 : Compile Date 03/08/24 @ 01:03AM AFLR3 : Copyright 1994-2021, D.L. Marcum AFLR3 : --------------------------------------- AFLR3 IC : INPUT SURFACE GRID CHECK AFLR3 IC : Nodes, Elements = 3366 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 FarField UG3 : 8 FarField UG3 : 9 FarField UG3 : 10 FarField UG3 : 11 FarField UG3 : 12 FarField AFLR3 : CPU Time = 0.010 seconds AFLR3 IG : INITIAL VOLUME GRID GENERATION AFLR3 IG : Nodes, Elements = 3366 0 AFLR3 IG : Nodes, Elements = 8 10 AFLR3 IG : Nodes, Elements = 674 4728 AFLR3 IG : Nodes, Elements = 1348 9669 AFLR3 IG : Nodes, Elements = 2022 14757 AFLR3 IG : Nodes, Elements = 2696 19981 AFLR3 IG : Nodes, Elements = 3370 24964 AFLR3 IG : Nodes, Elements = 3373 25026 AFLR3 IG : Nodes, Elements = 3373 24949 AFLR3 IG : Nodes, Elements = 3373 24685 AFLR3 IG : Nodes, Elements = 3373 21487 AFLR3 IG : Nodes, Elements = 3373 21486 AFLR3 IG : Nodes, Elements = 3373 24595 AFLR3 IG : Nodes, Elements = 3373 24517 AFLR3 IG : Nodes, Elements = 3373 20064 AFLR3 IG : Nodes, Elements = 3373 20063 AFLR3 IG : Nodes, Elements = 3366 10610 AFLR3 IG : Nodes, Elements = 3366 15316 AFLR3 IG : Nodes, Elements = 3366 8740 AFLR3 IG : Nodes, Elements = 3366 8166 AFLR3 : CPU Time = 0.208 seconds AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION AFLR3 GG : Nodes, Elements = 3366 8166 AFLR3 GG : Nodes, Elements = 3382 8214 AFLR3 GG : Nodes, Elements = 3382 8277 AFLR3 GG : Nodes, Elements = 3382 8116 AFLR3 GG : Nodes, Elements = 3390 8140 AFLR3 GG : Nodes, Elements = 3390 8226 AFLR3 GG : Nodes, Elements = 3390 8175 AFLR3 GG : Nodes, Elements = 3406 8223 AFLR3 GG : Nodes, Elements = 3406 8360 AFLR3 GG : Nodes, Elements = 3406 8286 AFLR3 GG : Nodes, Elements = 3428 8352 AFLR3 GG : Nodes, Elements = 3428 8525 AFLR3 GG : Nodes, Elements = 3428 8456 AFLR3 GG : Nodes, Elements = 3443 8501 AFLR3 GG : Nodes, Elements = 3443 8615 AFLR3 GG : Nodes, Elements = 3443 8545 AFLR3 GG : Nodes, Elements = 3451 8569 AFLR3 GG : Nodes, Elements = 3451 8632 AFLR3 GG : Nodes, Elements = 3451 8574 AFLR3 GG : Nodes, Elements = 3455 8586 AFLR3 GG : Nodes, Elements = 3455 8623 AFLR3 GG : Nodes, Elements = 3455 8601 AFLR3 GG : Nodes, Elements = 3456 8604 AFLR3 GG : Nodes, Elements = 3456 8613 AFLR3 GG : Nodes, Elements = 3456 8606 AFLR3 GG : Nodes, Elements = 3457 8609 AFLR3 GG : Nodes, Elements = 3457 8615 AFLR3 GG : Nodes, Elements = 3457 8611 AFLR3 : CPU Time = 0.040 seconds AFLR3 QI : QUALITY IMPROVEMENT AFLR3 QI : Nodes, Elements = 3457 8611 AFLR3 QI : Nodes, Elements = 3445 8536 AFLR3 QI : Nodes, Elements = 3443 8525 AFLR3 QI : Nodes, Elements = 3442 8520 AFLR3 QI : Nodes, Elements = 3442 13105 AFLR3 QI : Nodes, Elements = 3442 8947 AFLR3 QI : Nodes, Elements = 3442 8405 AFLR3 QI : Nodes, Elements = 3442 13072 AFLR3 QI : Nodes, Elements = 3442 8859 AFLR3 QI : Nodes, Elements = 3442 8402 AFLR3 QI : Nodes, Elements = 3442 13077 AFLR3 QI : Nodes, Elements = 3442 8914 AFLR3 QI : Nodes, Elements = 3442 8394 AFLR3 QI : Nodes, Elements = 3442 13082 AFLR3 QI : Nodes, Elements = 3442 8911 AFLR3 QI : Nodes, Elements = 3442 8401 AFLR3 QI : Nodes, Elements = 3442 13077 AFLR3 QI : Nodes, Elements = 3442 8868 AFLR3 QI : Nodes, Elements = 3442 8394 AFLR3 QI : Nodes, Elements = 3442 8278 AFLR3 QI : Nodes, Elements = 3465 8364 AFLR3 QI : Nodes, Elements = 3465 11774 AFLR3 QI : Nodes, Elements = 3465 8613 AFLR3 QI : Nodes, Elements = 3465 8248 AFLR3 QI : Nodes, Elements = 3465 11365 AFLR3 QI : Nodes, Elements = 3465 8551 AFLR3 QI : Nodes, Elements = 3465 8248 AFLR3 QI : Nodes, Elements = 3465 8364 AFLR3 : CPU Time = 0.285 seconds AFLR3 QRG: QUALITY GRID RE-GENERATION AFLR3 QRG: Nodes, Elements = 3465 8364 AFLR3 : CPU Time = 0.004 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 8364 UG3 : Min, Max Ang = 0.004058 179.4 UG3 : Average Angle = 73.8 UG3 : No. Angle>160.0 = 1604 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 3.72e+06 UG3 : No. Tet Elems = 8364 UG3 : Min Vol = 1.24e-07 UG3 : Average Vol = 445 UG3 : Total-Tet-Vol = 3.72e+06 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 = 8364 UG3 : Min, Max Q = 1.41e-05 0.995 UG3 : Average Q = 0.0492 UG3 : No. Q< 0.1 = 7623 UG3 : No. Q< 0.01 = 6479 OVERALL : CPU Time = 0.555 seconds UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 8364 UG3 : Min, Max Ang = 0.004058 179.4 UG3 : Average Angle = 73.8 UG3 : No. Angle>160.0 = 1604 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 3.72e+06 UG3 : No. Tet Elems = 8364 UG3 : Min Vol = 1.24e-07 UG3 : Average Vol = 445 UG3 : Total-Tet-Vol = 3.72e+06 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 = 8364 UG3 : Min, Max Q = 0.00273 1 UG3 : Average Q = 0.116 UG3 : No. Q< 0.1 = 6998 UG3 : No. Q< 0.01 = 5222 UG3 : CPU Time = 0.000 seconds EGADS : --------------------------------------- EGADS : Engineering Geometry Aircraft Design System EGADS : Version 1.25 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 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 1 EDGE 11 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 12 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 13 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 14 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 15 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 16 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 17 EGADS : CREATING TESSELLATION FOR BODY 1 EDGE 18 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 FACE 7 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 8 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 9 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 10 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 11 EGADS : CREATING TESSELLATION FOR BODY 1 FACE 12 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 1 FACE 7 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 8 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 9 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 10 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 11 EGADS : CHECKING NODE MAP FOR BODY 1 FACE 12 Volume mesh: Number of nodes = 3465 Number of elements = 15088 Number of triangles = 6724 Number of quadrilatarals = 0 Number of tetrahedrals = 8364 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 "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 10 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 7.74597 m. Reference origin for moment evaluation is (0.322749, 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. 3465 grid points. 8364 volume elements. 2 surface markers. 6712 boundary elements in index 0 (Marker = BC_1). 12 boundary elements in index 1 (Marker = BC_2). 8364 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: 3.71806e+06. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 219.454. Mean K: 28.4543. Standard deviation K: 38.6678. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.0682672| 83.7513| | CV Face Area Aspect Ratio| 1.01372| 6.97914e+07| | CV Sub-Volume Ratio| 1| 2.68778e+09| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 3465| 1/1.00| 10| | 1| 875| 1/3.96| 9.48112| | 2| 216| 1/4.05| 8.92139| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 19.2896 m^2. Area projection in the x-plane = 1.5163 m^2, y-plane = 0.798928 m^2, z-plane = 9.19279 m^2. Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399893 m. Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0331205 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| 1.0017e-01| -0.681171| 1.611951| 0.939583| 4.787935| 1.799036| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 9.7378e-02| 1.788949| 4.025943| 3.958053| 7.262923| 1.783801| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 9.7021e-02| 1.843258| 4.097916| 4.214487| 7.313930| 1.683865| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.0123e-01| 3.140367| 5.063738| 5.659695| 8.622083| 1.516280| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.0636e-01| 3.750531| 6.069799| 6.352102| 9.144076| 2.005401| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 3.75053| < -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 = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 265 Number of elements = 346 Number of triangle elements = 0 Number of quadrilateral elements = 346 ---------------------------- Total number of nodes = 265 Total number of elements = 346 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 = 2 Name = ritePointLoad, index = 1 Name = leftPointLoad, 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 = 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 = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 265 Number of elements = 346 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 346 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 CAPS Info: Reparameterization Bound -> upperWing -- nu, nv = 33 129 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 3358 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure' Rank 0: src = 6.231956e+09, tgt = 6.231956e+09, diff = 1.099608e+01 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 3358 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure' Rank 0: src = 6.052604e+09, tgt = 6.052604e+09, diff = 1.772976e-02 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 3358 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure' Rank 0: src = 6.196951e+07, tgt = 6.196951e+07, diff = 0.000000e+00 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 3358 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure' Rank 0: src = 6.216080e+07, tgt = 6.216080e+07, diff = 7.450581e-09 Extracting external pressure loads from data transfer.... TransferName = upperWing Number of Elements = 96 (total = 96) Extracting external pressure loads from data transfer.... TransferName = lowerWing Number of Elements = 96 (total = 192) Extracting external pressure loads from data transfer.... TransferName = leftTip Number of Elements = 10 (total = 202) Extracting external pressure loads from data transfer.... TransferName = riteTip Number of Elements = 10 (total = 212) 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...... ==> 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 "BlackBird (7.5.1) " Running SU2...... ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Mesh Deformation Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- ----------------- Physical Case Definition ( Zone 0 ) ------------------- Input mesh file name: ../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. 3465 grid points. 8364 volume elements. 2 surface markers. 6712 boundary elements in index 0 (Marker = BC_1). 12 boundary elements in index 1 (Marker = BC_2). 8364 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: 3.71806e+06. Info: Ignoring the following volume output fields/groups: SOLUTION Volume output fields: COORDINATES Info: Ignoring the following screen output fields: RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME Info: Ignoring the following history output groups: RMS_RES, AERO_COEFF History output group(s): ITER, TIME_DOMAIN, WALL_TIME 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 0.184310 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 10 m^2. The semi-span will be computed using the max y(3D) value. The reference length is 7.74597 m. Reference origin for moment evaluation is (0.322749, 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. 3465 grid points. 8364 volume elements. 2 surface markers. 6712 boundary elements in index 0 (Marker = BC_1). 12 boundary elements in index 1 (Marker = BC_2). 8364 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 5570 TETRAHEDRON volume elements. There has been a re-orientation of 4755 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 1.87517e+15. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 2.57124. Mean K: 0.00792579. Standard deviation K: 0.0526201. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.000599781| 57.948| | CV Face Area Aspect Ratio| 1.57004| 7.296e+07| | CV Sub-Volume Ratio| 1.00071| 3.24709e+12| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 3465| 1/1.00| 10| | 1| 879| 1/3.94| 9.49554| | 2| 216| 1/4.07| 8.92139| +-------------------------------------------+ Finding max control volume width. Semi-span length = 32735.3 m. Wetted area = 6.66529e+10 m^2. Area projection in the x-plane = 4.03065e+10 m^2, y-plane = 6.63616e+09 m^2, z-plane = 2.10012e+09 m^2. Max. coordinate in the x-direction = 141.51 m, y-direction = 32735.3 m, z-direction = 810013 m. Min. coordinate in the x-direction = -42891.9 m, y-direction = -43118 m, z-direction = -25310.1 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| 9.3924e-02| 10.812146| 13.784763| 13.851802| 16.281252| 0.056571| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 9.4178e-02| 10.817161| 13.625238| 13.582942| 16.204314| 0.053695| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 9.4137e-02| 10.891144| 13.588039| 13.499728| 16.280929| 0.054169| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 9.4046e-02| 10.857903| 13.503155| 13.563692| 16.247091| 0.053993| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 9.4092e-02| 10.880881| 13.456688| 13.541369| 16.337336| 0.053517| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 10.8809| < -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 382 non-physical points in the solution. Warning: 271 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 = 3358 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure' Rank 0: src = 4.505314e+09, tgt = 4.505315e+09, diff = 1.426678e+03 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 3358 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure' Rank 0: src = 3.466032e+09, tgt = 3.466032e+09, diff = 3.271767e+00 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 3358 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure' Rank 0: src = 2.711999e+07, tgt = 2.711999e+07, diff = 1.788139e-07 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 3358 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure' Rank 0: src = 1.209191e+07, tgt = 1.209191e+07, diff = 1.117587e-08 Extracting external pressure loads from data transfer.... TransferName = upperWing Number of Elements = 96 (total = 96) Extracting external pressure loads from data transfer.... TransferName = lowerWing Number of Elements = 96 (total = 192) Extracting external pressure loads from data transfer.... TransferName = leftTip Number of Elements = 10 (total = 202) Extracting external pressure loads from data transfer.... TransferName = riteTip Number of Elements = 10 (total = 212) 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...... ==> Running ASTROS post-analysis... real 0m25.606s user 0m30.967s sys 1m35.359s + status=0 + set +x ================================================= data/session11/aeroelastic_2_Iterative_SU2_Astros.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Did not run examples for: session08 fun3d session11 fun3d+astros ================================================= ================================================= Summary of examples NOT finished as expected data/session10/nastran_5_Flutter.py See training.log for more details. ================================================= Build step 'Conditional step (single)' 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