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Full Logsee 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| 6.6934e+00| 0.947347| 3.223903| 2.943322| 6.430193| -0.383883| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 6.6863e+00| 1.104824| 3.558510| 3.286305| 6.595987| 0.086546| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 6.6485e+00| 1.232714| 3.743196| 3.559847| 6.721966| 1.654776| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 6.6734e+00| 1.284073| 3.845764| 3.673420| 6.769485| 7.084177| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 6.6570e+00| 1.323585| 3.917154| 3.736002| 6.807014| 35.803741| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 1.32358| < -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 = 0.3226 Cd = 0.00901 --> Cmx = -7.3e-05 Cmy = -0.052999 Cmz = -9e-05 --> Cx = 0.003379 Cy = -0.000277 Cz = 0.322708 real 1m39.394s user 1m22.445s sys 0m7.371s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) real 0m22.297s user 0m22.905s sys 0m2.332s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 = 11079 Number of elements = 22781 Number of triangle elements = 22781 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11079 Total number of elements = 22781 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 = 11911 Number of elements = 24445 Number of triangle elements = 24445 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11911 Total number of elements = 24445 real 0m21.042s user 0m23.551s sys 0m2.687s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 = 731 Number of elements = 1779 Number of triangle elements = 1779 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 731 Total number of elements = 1779 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 = 3548 Number of elements = 7675 Number of triangle elements = 7675 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3548 Total number of elements = 7675 real 0m19.806s user 0m21.074s sys 0m2.465s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 = 1405 Number of elements = 3135 Number of triangle elements = 3135 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 1405 Total number of elements = 3135 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 = 2096 Number of elements = 4568 Number of triangle elements = 4568 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 2096 Total number of elements = 4568 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 0m21.252s user 0m23.124s sys 0m2.927s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 = 3559 Number of elements = 7459 Number of triangle elements = 7459 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3559 Total number of elements = 7459 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 = 12395 Number of elements = 25258 Number of triangle elements = 25258 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 12395 Total number of elements = 25258 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 = 44950 Number of elements = 90567 Number of triangle elements = 90567 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 44950 Total number of elements = 90567 real 0m28.599s user 0m34.400s sys 0m3.217s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 = 8299 Number of elements = 17185 Number of triangle elements = 17185 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 8299 Total number of elements = 17185 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 ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 0m35.063s user 0m35.468s sys 0m3.447s + status=0 + set +x ================================================= data/session09/tess_6_TriQuad.py passed (as expected) ================================================= ================================================= tess_7_MeshSizing.py test; + python tess_7_MeshSizing.py + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 = 8299 Number of elements = 17185 Number of triangle elements = 17185 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 8299 Total number of elements = 17185 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 = 3890 Number of elements = 8352 Number of triangle elements = 8352 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3890 Total number of elements = 8352 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 0m20.393s user 0m22.953s sys 0m3.022s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 = 6585 Number of elements = 13196 Number of triangle elements = 13196 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 6585 Total number of elements = 13196 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 = 22194 Number of elements = 22195 Number of triangle elements = 0 Number of quadrilateral elements = 22195 ---------------------------- Total number of nodes = 22194 Total number of elements = 22195 real 0m22.612s user 0m25.102s sys 0m2.960s + status=0 + set +x ================================================= data/session09/tess_8_MeshSizing.py passed (as expected) ================================================= ================================================= tess_MinQuad.py test; + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log + python tess_MinQuad.py ==> Loading geometry from file "../../data/ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 0m16.514s user 0m18.308s sys 0m2.631s + status=0 + set +x ================================================= solutions/session09/tess_MinQuad.py passed (as expected) ================================================= ================================================= tess_2k.py test; + python tess_2k.py + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../../data/ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 0m17.800s user 0m19.490s sys 0m2.505s + status=0 + set +x ================================================= solutions/session09/tess_2k.py passed (as expected) ================================================= ================================================= astros_1_ModalClamped.py test; + python astros_1_ModalClamped.py + tee -a /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ==> Running ASTROS pre-analysis... ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 : 0.0357647 3 : 0.102451 4 : 0.102451 5 : 0.159637 6 : 0.159637 7 : 0.215446 8 : 0.215446 9 : 0.350115 10: 0.350115 real 0m29.202s user 0m24.821s sys 0m7.351s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ==> Running ASTROS pre-analysis... ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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 : 0.0357647 2 : 0.0365801 3 : 0.102451 4 : 0.102453 5 : 0.159637 6 : 0.1611 7 : 0.215446 8 : 0.215462 9 : 0.350115 10: 0.351196 real 0m32.730s user 0m26.459s sys 0m9.111s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ==> Running ASTROS pre-analysis... ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL --> Maximum displacements: --> Tmax 43461.879162311016 --> T1max 738.595 --> T2max 3686.25 --> T3max 43363.8 real 0m19.985s user 0m20.539s sys 0m3.586s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ==> Running ASTROS pre-analysis... ERROR:: (edge_not_found) in Branch Brch_000207 at [[/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]] SELECT specified nonexistant Edge --> catching signal -223 (edge_not_found) 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... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL --> Maximum displacements: --> Tmax 12131.654370141774 --> T1max 275.241 --> T2max 1005.74 --> T3max 12103.5 real 0m17.408s user 0m18.480s sys 0m2.862s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ==> 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: nastran: command not found Traceback (most recent call last): File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/data/session10/nastran_5_Flutter.py", line 138, in <module> nastran.postAnalysis() File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/pyCAPS/pyCAPS/problem.py", line 2159, in postAnalysis self._analysisObj.postAnalysis() File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed return func(*args, **kwargs) ^^^^^^^^^^^^^^^^^^^^^ File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/pyCAPS/pyCAPS/caps.py", line 2913, in postAnalysis if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs)) ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^ File "/Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/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 0m18.292s user 0m18.834s sys 0m3.332s + 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 /Users/jenkins/workspace/ESP_RegCaps/7.8/CAPS/training/DARWIN64/CAPS/training/training.log Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found Information: Dynamic Loader for scribeWake.so not found dlopen(scribeWake.so, 130): image not found ==> 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 9.14.7 AFLR2 : Version Date 07/16/23 @ 01:42PM AFLR2 : Compile OS Darwin 22.5.0 x86_64 AFLR2 : Compile Date 07/25/23 @ 11:59AM 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 11.5.9 AFLR4 : Version Date 08/14/23 @ 12:27AM AFLR4 : Compile OS Darwin 22.5.0 x86_64 AFLR4 : Compile Date 08/14/23 @ 01:13PM 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 Sense Edges EGADS : 1 Yes 1 -1 2 3 -4 EGADS : 2 Yes 1 -3 5 1 -6 EGADS : 3 Yes 1 4 6 EGADS : 4 Yes 1 7 9 -8 -2 EGADS : 5 Yes 1 8 10 -7 -5 EGADS : 6 Yes 1 -9 -10 EGADS : 7 Yes 1 11 12 -13 -14 EGADS : 8 Yes 1 -15 18 17 -16 EGADS : 9 Yes 1 19 15 -20 -11 EGADS : 10 Yes 1 -21 13 22 -17 EGADS : 11 Yes 1 14 21 -18 -19 EGADS : 12 Yes 1 -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 = 6.45497 AFLR4 : BL Thickness = 0 AFLR4 : FarField Spacing = 21.0478 AFLR4 : Abs Min Surf Spacing = 0.0161374 AFLR4 : Min Surf Spacing = 0.0322749 AFLR4 : Max Surf Spacing = 0.645497 AFLR4 : Global Scale Factor = 1 AFLR4 : Geometry Definition Information AFLR4 : Definition Definition Composite Grid BC AFLR4 : ID Type ID Type AFLR4 : 0 glue-only composite - - AFLR4 : 1 CAD geometry 0 STD w/BL AFLR4 : 2 CAD geometry 0 STD w/BL AFLR4 : 3 CAD geometry 0 STD w/BL AFLR4 : 4 CAD geometry 0 STD w/BL AFLR4 : 5 CAD geometry 0 STD w/BL AFLR4 : 6 CAD geometry 0 STD w/BL AFLR4 : 7 CAD geometry 0 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= 1658 3135 0 AFLR4 : Nodes, Trias,Quads= 971 1761 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 1628 3077 0 AFLR4 : Nodes, Trias,Quads= 941 1703 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 48 65 0 AFLR4 : Nodes, Trias,Quads= 44 57 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 1668 3155 0 AFLR4 : Nodes, Trias,Quads= 986 1791 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 1625 3071 0 AFLR4 : Nodes, Trias,Quads= 930 1681 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 48 65 0 AFLR4 : Nodes, Trias,Quads= 44 57 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 3847 7686 938 AFLR4 : Curvature BG Surface Grid Generation AFLR4 : Nodes, Faces = 3847 7686 AFLR4 : Surface Grid Generation AFLR4 : Generate optimal mesh on surface definition 1 AFLR2 : Nodes, Trias,Quads= 3367 6423 0 AFLR4 : Nodes, Trias,Quads= 2401 4491 0 AFLR4 : Generate optimal mesh on surface definition 2 AFLR2 : Nodes, Trias,Quads= 3394 6478 0 AFLR4 : Nodes, Trias,Quads= 2282 4254 0 AFLR4 : Generate optimal mesh on surface definition 3 AFLR2 : Nodes, Trias,Quads= 145 226 0 AFLR4 : Nodes, Trias,Quads= 131 198 0 AFLR4 : Generate optimal mesh on surface definition 4 AFLR2 : Nodes, Trias,Quads= 3366 6421 0 AFLR4 : Nodes, Trias,Quads= 2394 4477 0 AFLR4 : Generate optimal mesh on surface definition 5 AFLR2 : Nodes, Trias,Quads= 3405 6500 0 AFLR4 : Nodes, Trias,Quads= 2289 4268 0 AFLR4 : Generate optimal mesh on surface definition 6 AFLR2 : Nodes, Trias,Quads= 145 226 0 AFLR4 : Nodes, Trias,Quads= 131 198 0 AFLR4 : Generate optimal mesh on surface definition 7 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 8 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 9 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 10 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 11 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 AFLR4 : Generate optimal mesh on surface definition 12 AFLR2 : Nodes, Trias,Quads= 73 116 0 AFLR4 : Nodes, Trias,Quads= 68 106 0 DGEOM : Add surface definitions to composite definition 0 DGEOM : Glue composite surface definition 0 DGEOM : Nodes,Faces,BEdges= 9265 18522 1526 OVERALL : CPU Time = 0.380 seconds Body 1 (of 2) Number of nodes = 8945 Number of elements = 17886 Number of triangle elements = 17886 Number of quadrilateral elements = 0 Body 2 (of 2) Number of nodes = 320 Number of elements = 636 Number of triangle elements = 636 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 9265 Total number of elements = 18522 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 9.14.7 AFLR2 : Version Date 07/16/23 @ 01:42PM AFLR2 : Compile OS Darwin 22.5.0 x86_64 AFLR2 : Compile Date 07/25/23 @ 11:59AM 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 11.5.9 AFLR4 : Version Date 08/14/23 @ 12:27AM AFLR4 : Compile OS Darwin 22.5.0 x86_64 AFLR4 : Compile Date 08/14/23 @ 01:13PM 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 Sense Edges EGADS : 1 Yes 1 -1 2 3 -4 EGADS : 2 Yes 1 -3 5 1 -6 EGADS : 3 Yes 1 4 6 EGADS : 4 Yes 1 7 9 -8 -2 EGADS : 5 Yes 1 8 10 -7 -5 EGADS : 6 Yes 1 -9 -10 EGADS : 7 Yes 1 11 12 -13 -14 EGADS : 8 Yes 1 -15 18 17 -16 EGADS : 9 Yes 1 19 15 -20 -11 EGADS : 10 Yes 1 -21 13 22 -17 EGADS : 11 Yes 1 14 21 -18 -19 EGADS : 12 Yes 1 -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= 18522 AFLR43 : Nodes = 9265 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 16.32.49 AFLR3 : Version Date 07/26/23 @ 12:32AM AFLR3 : Compile OS Darwin 22.5.0 x86_64 AFLR3 : Compile Date 07/26/23 @ 01:42PM AFLR3 : Copyright 1994-2021, D.L. Marcum AFLR3 : --------------------------------------- AFLR3 IC : INPUT SURFACE GRID CHECK AFLR3 IC : Nodes, Elements = 9265 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 = 0.031 seconds AFLR3 IG : INITIAL VOLUME GRID GENERATION AFLR3 IG : Nodes, Elements = 9265 0 AFLR3 IG : Nodes, Elements = 8 10 AFLR3 IG : Nodes, Elements = 1854 12751 AFLR3 IG : Nodes, Elements = 3708 26146 AFLR3 IG : Nodes, Elements = 5562 39560 AFLR3 IG : Nodes, Elements = 7416 54219 AFLR3 IG : Nodes, Elements = 9270 69439 AFLR3 IG : Nodes, Elements = 9272 69506 AFLR3 IG : Nodes, Elements = 9272 69327 AFLR3 IG : Nodes, Elements = 9265 42264 AFLR3 IG : Nodes, Elements = 9265 42329 AFLR3 IG : Nodes, Elements = 9265 30527 AFLR3 IG : Nodes, Elements = 9265 28352 AFLR3 : CPU Time = 0.396 seconds AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION AFLR3 GG : Nodes, Elements = 9265 28352 AFLR3 GG : Nodes, Elements = 13506 41142 AFLR3 GG : Nodes, Elements = 13506 58138 AFLR3 GG : Nodes, Elements = 13506 53658 AFLR3 GG : Nodes, Elements = 17029 64627 AFLR3 GG : Nodes, Elements = 17029 78502 AFLR3 GG : Nodes, Elements = 17029 74033 AFLR3 GG : Nodes, Elements = 20551 85011 AFLR3 GG : Nodes, Elements = 20551 98357 AFLR3 GG : Nodes, Elements = 20551 94217 AFLR3 GG : Nodes, Elements = 24250 105402 AFLR3 GG : Nodes, Elements = 24250 120229 AFLR3 GG : Nodes, Elements = 24250 116095 AFLR3 GG : Nodes, Elements = 28002 127433 AFLR3 GG : Nodes, Elements = 28002 142141 AFLR3 GG : Nodes, Elements = 28002 138311 AFLR3 GG : Nodes, Elements = 31682 149402 AFLR3 GG : Nodes, Elements = 31682 164014 AFLR3 GG : Nodes, Elements = 31682 160159 AFLR3 GG : Nodes, Elements = 35282 171018 AFLR3 GG : Nodes, Elements = 35282 185157 AFLR3 GG : Nodes, Elements = 35282 181563 AFLR3 GG : Nodes, Elements = 38752 192024 AFLR3 GG : Nodes, Elements = 38752 205588 AFLR3 GG : Nodes, Elements = 38752 202042 AFLR3 GG : Nodes, Elements = 42058 212005 AFLR3 GG : Nodes, Elements = 42058 225002 AFLR3 GG : Nodes, Elements = 42058 221703 AFLR3 GG : Nodes, Elements = 45263 231360 AFLR3 GG : Nodes, Elements = 45263 243903 AFLR3 GG : Nodes, Elements = 45263 240753 AFLR3 GG : Nodes, Elements = 48312 249912 AFLR3 GG : Nodes, Elements = 48312 261837 AFLR3 GG : Nodes, Elements = 48312 258778 AFLR3 GG : Nodes, Elements = 51253 267618 AFLR3 GG : Nodes, Elements = 51253 278991 AFLR3 GG : Nodes, Elements = 51253 276270 AFLR3 GG : Nodes, Elements = 53997 284512 AFLR3 GG : Nodes, Elements = 53997 295301 AFLR3 GG : Nodes, Elements = 53997 292617 AFLR3 GG : Nodes, Elements = 56636 300544 AFLR3 GG : Nodes, Elements = 56636 310885 AFLR3 GG : Nodes, Elements = 56636 308283 AFLR3 GG : Nodes, Elements = 59100 315680 AFLR3 GG : Nodes, Elements = 59100 325300 AFLR3 GG : Nodes, Elements = 59100 322909 AFLR3 GG : Nodes, Elements = 61369 329721 AFLR3 GG : Nodes, Elements = 61369 338622 AFLR3 GG : Nodes, Elements = 61369 336403 AFLR3 GG : Nodes, Elements = 63529 342893 AFLR3 GG : Nodes, Elements = 63529 351382 AFLR3 GG : Nodes, Elements = 63529 349295 AFLR3 GG : Nodes, Elements = 65528 355300 AFLR3 GG : Nodes, Elements = 65528 363030 AFLR3 GG : Nodes, Elements = 65528 361177 AFLR3 GG : Nodes, Elements = 67366 366693 AFLR3 GG : Nodes, Elements = 67366 373872 AFLR3 GG : Nodes, Elements = 67366 372130 AFLR3 GG : Nodes, Elements = 69090 377304 AFLR3 GG : Nodes, Elements = 69090 384000 AFLR3 GG : Nodes, Elements = 69090 382333 AFLR3 GG : Nodes, Elements = 70683 387115 AFLR3 GG : Nodes, Elements = 70683 393302 AFLR3 GG : Nodes, Elements = 70683 391819 AFLR3 GG : Nodes, Elements = 72174 396293 AFLR3 GG : Nodes, Elements = 72174 402104 AFLR3 GG : Nodes, Elements = 72174 400678 AFLR3 GG : Nodes, Elements = 73511 404691 AFLR3 GG : Nodes, Elements = 73511 409976 AFLR3 GG : Nodes, Elements = 73511 408640 AFLR3 GG : Nodes, Elements = 74708 412232 AFLR3 GG : Nodes, Elements = 74708 416933 AFLR3 GG : Nodes, Elements = 74708 415779 AFLR3 GG : Nodes, Elements = 75704 418768 AFLR3 GG : Nodes, Elements = 75704 422708 AFLR3 GG : Nodes, Elements = 75704 421707 AFLR3 GG : Nodes, Elements = 76562 424282 AFLR3 GG : Nodes, Elements = 76562 427711 AFLR3 GG : Nodes, Elements = 76562 426848 AFLR3 GG : Nodes, Elements = 77202 428768 AFLR3 GG : Nodes, Elements = 77202 431402 AFLR3 GG : Nodes, Elements = 77202 430643 AFLR3 GG : Nodes, Elements = 77612 431874 AFLR3 GG : Nodes, Elements = 77612 433592 AFLR3 GG : Nodes, Elements = 77612 433078 AFLR3 GG : Nodes, Elements = 77859 433820 AFLR3 GG : Nodes, Elements = 77859 434829 AFLR3 GG : Nodes, Elements = 77859 434519 AFLR3 GG : Nodes, Elements = 78008 434966 AFLR3 GG : Nodes, Elements = 78008 435571 AFLR3 GG : Nodes, Elements = 78008 435391 AFLR3 GG : Nodes, Elements = 78079 435604 AFLR3 GG : Nodes, Elements = 78079 435902 AFLR3 GG : Nodes, Elements = 78079 435807 AFLR3 GG : Nodes, Elements = 78119 435927 AFLR3 GG : Nodes, Elements = 78119 436084 AFLR3 GG : Nodes, Elements = 78119 436033 AFLR3 GG : Nodes, Elements = 78141 436099 AFLR3 GG : Nodes, Elements = 78141 436179 AFLR3 GG : Nodes, Elements = 78141 436154 AFLR3 GG : Nodes, Elements = 78149 436178 AFLR3 GG : Nodes, Elements = 78149 436214 AFLR3 GG : Nodes, Elements = 78149 436202 AFLR3 GG : Nodes, Elements = 78152 436211 AFLR3 GG : Nodes, Elements = 78152 436224 AFLR3 GG : Nodes, Elements = 78152 436216 AFLR3 GG : Nodes, Elements = 78159 436237 AFLR3 GG : Nodes, Elements = 78159 436271 AFLR3 GG : Nodes, Elements = 78159 436259 AFLR3 GG : Nodes, Elements = 78162 436268 AFLR3 GG : Nodes, Elements = 78162 436278 AFLR3 GG : Nodes, Elements = 78162 436274 AFLR3 GG : Nodes, Elements = 78169 436295 AFLR3 GG : Nodes, Elements = 78169 436322 AFLR3 GG : Nodes, Elements = 78169 436312 AFLR3 GG : Nodes, Elements = 78170 436315 AFLR3 GG : Nodes, Elements = 78170 436318 AFLR3 : CPU Time = 6.585 seconds AFLR3 QI : QUALITY IMPROVEMENT AFLR3 QI : Nodes, Elements = 78170 436318 AFLR3 QI : Nodes, Elements = 77790 434173 AFLR3 QI : Nodes, Elements = 77715 433738 AFLR3 QI : Nodes, Elements = 77703 433672 AFLR3 QI : Nodes, Elements = 77701 433659 AFLR3 QI : Nodes, Elements = 77701 435676 AFLR3 QI : Nodes, Elements = 77701 433539 AFLR3 QI : Nodes, Elements = 77701 432733 AFLR3 QI : Nodes, Elements = 77701 432971 AFLR3 QI : Nodes, Elements = 77701 432584 AFLR3 QI : Nodes, Elements = 77701 432481 AFLR3 : CPU Time = 1.524 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 432481 UG3 : Min, Max Ang = 11.86 154.9 UG3 : Average Angle = 70.2 UG3 : No. Angle>160.0 = 0 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 3.72e+06 UG3 : No. Tet Elems = 432481 UG3 : Min Vol = 9.83e-07 UG3 : Average Vol = 8.6 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 = 432481 UG3 : Min, Max Q = 0.279 1 UG3 : Average Q = 0.895 UG3 : No. Q< 0.1 = 0 UG3 : No. Q< 0.01 = 0 OVERALL : CPU Time = 8.739 seconds UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 432481 UG3 : Min, Max Ang = 11.86 154.9 UG3 : Average Angle = 70.2 UG3 : No. Angle>160.0 = 0 UG3 : No. Angle>179.9 = 0 UG3 : VOL CHECK UG3 : Total-Volume = 3.72e+06 UG3 : No. Tet Elems = 432481 UG3 : Min Vol = 9.83e-07 UG3 : Average Vol = 8.6 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 = 432481 UG3 : Min, Max Q = 0.453 1 UG3 : Average Q = 0.873 UG3 : No. Q< 0.1 = 0 UG3 : No. Q< 0.01 = 0 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 = 77701 Number of elements = 451003 Number of triangles = 18522 Number of quadrilatarals = 0 Number of tetrahedrals = 432481 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_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_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. 77701 grid points. 432481 volume elements. 2 surface markers. 17886 boundary elements in index 0 (Marker = BC_1). 636 boundary elements in index 1 (Marker = BC_2). 432481 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: 431.689. Mean K: 20.6913. Standard deviation K: 49.4453. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 53.8784| 86.5125| | CV Face Area Aspect Ratio| 1.09483| 87.0571| | CV Sub-Volume Ratio| 1| 982.633| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 77701| 1/1.00| 10| | 1| 12754| 1/6.09| 8.21293| | 2| 1943| 1/6.56| 6.57958| +-------------------------------------------+ Finding max control volume width. Semi-span length = 3.87298 m. Wetted area = 20.5583 m^2. Area projection in the x-plane = 1.52985 m^2, y-plane = 0.868532 m^2, z-plane = 9.83638 m^2. Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399868 m. Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0329598 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| 3.9064e+00| -1.752738| 0.465242| 0.065960| 3.716367| -0.557295| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.4397e+00| -1.528709| 0.867298| 0.583756| 3.946161| -0.298906| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.3746e+00| -1.569594| 0.964065| 0.772248| 3.899884| 1.824052| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.3702e+00| -1.661588| 0.961925| 0.802233| 3.801802| -8.292456| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.3730e+00| -1.623916| 0.890904| 0.740803| 3.841981| -5.283484| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.62392| < -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 = 129 129 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 8945 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure' Rank 0: src = 6.248289e+09, tgt = 6.248289e+09, diff = 8.295603e-01 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 8945 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure' Rank 0: src = 6.101661e+09, tgt = 6.101661e+09, diff = 4.711933e-01 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 8945 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure' Rank 0: src = 6.120537e+07, tgt = 6.120537e+07, diff = 2.235174e-08 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 8945 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure' Rank 0: src = 6.124007e+07, tgt = 6.124007e+07, diff = 1.862645e-07 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...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running ASTROS post-analysis... ==> Running SU2 pre-analysis... Writing boundary flags - bcProps.surfaceProp[0].surfaceType = 3 - bcProps.surfaceProp[1].surfaceType = 1 Done boundary flags Writing SU2 data transfer files Writing SU2 Motion File - aeroelasticIterative_motion.dat Warning: The su2 cfg file will be overwritten! Write SU2 configuration file for version "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_0.su2 ---------------- Grid deformation parameters ( Zone 0 ) ---------------- Grid deformation using a linear elasticity method. -------------------- Output Information ( Zone 0 ) ---------------------- Output mesh file name: ../aflr3/aflr3_0.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. 77701 grid points. 432481 volume elements. 2 surface markers. 17886 boundary elements in index 0 (Marker = BC_1). 636 boundary elements in index 1 (Marker = BC_2). 432481 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 28.993880 seconds on 1 core. ----------------------- Write deformed grid files ----------------------- |SU2 mesh |../aflr3/aflr3_0.su2 | |CSV file |surface_deformed.csv | |Tecplot binary |volume_deformed.szplt | |Tecplot binary surface |surface_deformed.szplt | Adding any FFD information to the SU2 file. ------------------------- Finalize Solver ------------------------- Deleted CNumerics container. Deleted CSolver container. Deleted CGeometry container. Deleted CSurfaceMovement class. Deleted CVolumetricMovement class. Deleted CConfig container. Deleted COutput class. ------------------------- Exit Success (SU2_DEF) ------------------------ ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) Release 8.0.0 "Harrier" | | \__ \ |_| |/ / | | |___/\___//___| Suite (Computational Fluid Dynamics Code) | | | ------------------------------------------------------------------------- | SU2 Project Website: https://su2code.github.io | | | | The SU2 Project is maintained by the SU2 Foundation | | (http://su2foundation.org) | ------------------------------------------------------------------------- | Copyright 2012-2023, SU2 Contributors | | | | SU2 is free software; you can redistribute it and/or | | modify it under the terms of the GNU Lesser General Public | | License as published by the Free Software Foundation; either | | version 2.1 of the License, or (at your option) any later version. | | | | SU2 is distributed in the hope that it will be useful, | | but WITHOUT ANY WARRANTY; without even the implied warranty of | | MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU | | Lesser General Public License for more details. | | | | You should have received a copy of the GNU Lesser General Public | | License along with SU2. If not, see <http://www.gnu.org/licenses/>. | ------------------------------------------------------------------------- Parsing config file for zone 0 ----------------- Physical Case Definition ( Zone 0 ) ------------------- Compressible Euler equations. Mach number: 0.294118. Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg. No restart solution, use the values at infinity (freestream). Dimensional simulation. The reference area is 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_0.su2 --------------- Space Numerical Integration ( Zone 0 ) ------------------ Roe (with entropy fix = 0.001) solver for the flow inviscid terms. Standard Roe without low-dissipation function. Second order integration in space, with slope limiter. Venkatakrishnan slope-limiting method, with constant: 0.05. The reference element size is: 1. Gradient for upwind reconstruction: inverse-distance weighted Least-Squares. Gradient for viscous and source terms: inverse-distance weighted Least-Squares. --------------- Time Numerical Integration ( Zone 0 ) ------------------ Local time stepping (steady state simulation). Euler implicit method for the flow equations. FGMRES is used for solving the linear system. Using a ILU(0) preconditioning. Convergence criteria of the linear solver: 1e-06. Max number of linear iterations: 10. V Multigrid Cycle, with 2 multigrid levels. Damping factor for the residual restriction: 0.75. Damping factor for the correction prolongation: 0.75. No CFL adaptation. +-------------------------------------------+ | MG Level| Presmooth|PostSmooth|CorrectSmo| +-------------------------------------------+ | 0| 1| 0| 0| | 1| 2| 0| 0| | 2| 3| 0| 0| +-------------------------------------------+ Courant-Friedrichs-Lewy number: 10 ------------------ Convergence Criteria ( Zone 0 ) --------------------- Maximum number of solver subiterations: 5. Begin convergence monitoring at iteration 5. Residual minimum value: 1e-14. Cauchy series min. value: 1e-10. Number of Cauchy elements: 100. Begin windowed time average at iteration 0. -------------------- Output Information ( Zone 0 ) ---------------------- File writing frequency: +------------------------------------+ | File| Frequency| +------------------------------------+ | RESTART| 250| | SURFACE_CSV| 250| | TECPLOT| 250| | SURFACE_TECPLOT| 250| +------------------------------------+ Writing the convergence history file every 1 inner iterations. Writing the screen convergence history every 1 inner iterations. The tabular file format is CSV (.csv). Convergence history file name: history. Forces breakdown file name: forces_breakdown_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. 77701 grid points. 432481 volume elements. 2 surface markers. 17886 boundary elements in index 0 (Marker = BC_1). 636 boundary elements in index 1 (Marker = BC_2). 432481 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 197203 TETRAHEDRON volume elements. There has been a re-orientation of 4593 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 1.45199e+17. Searching for the closest normal neighbors to the surfaces. Storing a mapping from global to local point index. Compute the surface curvature. Max K: 3.07719. Mean K: 0.00655943. Standard deviation K: 0.0480359. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.0486509| 82.3268| | CV Face Area Aspect Ratio| 1.84126| 1.87689e+06| | CV Sub-Volume Ratio| 1| 1.34334e+08| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 77701| 1/1.00| 10| | 1| 12784| 1/6.08| 8.21936| | 2| 1953| 1/6.55| 6.59084| +-------------------------------------------+ Finding max control volume width. Semi-span length = 80063.6 m. Wetted area = 2.58701e+11 m^2. Area projection in the x-plane = 1.15382e+11 m^2, y-plane = 3.58648e+10 m^2, z-plane = 2.99408e+09 m^2. Max. coordinate in the x-direction = 3912.17 m, y-direction = 80063.6 m, z-direction = 0.130929 m. Min. coordinate in the x-direction = -24304.8 m, y-direction = -119977 m, z-direction = -1.4803e+06 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| 3.8874e+00| 11.166537| 14.130869| 14.016169| 16.635643| 0.011118| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.7822e+00| 11.300027| 14.044344| 13.931107| 16.735292| 0.015863| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.7167e+00| 11.480874| 14.083394| 14.014218| 16.879865| -0.048654| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.6750e+00| 11.587488| 14.257307| 14.043147| 16.996105| 0.002654| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.6595e+00| 11.641522| 14.317555| 14.096039| 17.080511| -0.003661| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 11.6415| < -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 3614 non-physical points in the solution. Warning: 982 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 = 8945 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure' Rank 0: src = 3.392108e+09, tgt = 3.392108e+09, diff = 4.135114e+01 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 8945 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure' Rank 0: src = 3.475997e+09, tgt = 3.475997e+09, diff = 2.307168e+01 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 8945 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure' Rank 0: src = 1.744463e+07, tgt = 1.744463e+07, diff = 0.000000e+00 Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv Number of variables = 16 Number of data points = 8945 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure' Rank 0: src = 2.282920e+07, tgt = 2.282920e+07, diff = 1.970679e-06 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...... Note: The following floating-point exceptions are signalling: IEEE_UNDERFLOW_FLAG IEEE_DENORMAL ==> Running ASTROS post-analysis... real 3m29.930s user 3m2.019s sys 0m13.072s + status=0 + set +x ================================================= data/session11/aeroelastic_2_Iterative_SU2_Astros.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Did not run examples for: session07 pointwise session08 fun3d session11 fun3d+astros ================================================= ================================================= Summary of examples NOT finished as expected data/session06/aflr4_aflr3_09_InviscidWing.py data/session06/aflr4_aflr3_10_ViscousWing.py data/session06/aflr4_aflr3_11_ViscousWingPod.py data/session06/aflr4_aflr3_12_ViscousTransport.py 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