The Jenkins Controller is preparing for shutdown. No new builds can be started.
Skipping 2,068 KB.. Full Log--> 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 = 11092 Number of elements = 22807 Number of triangle elements = 22807 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11092 Total number of elements = 22807 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 11921 Number of elements = 24465 Number of triangle elements = 24465 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 11921 Total number of elements = 24465 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m32.233s user 0m54.916s sys 2m29.961s + status=0 + set +x ================================================= data/session09/tess_2_TFI_Templates.py passed (as expected) ================================================= ================================================= tess_3_Params.py test; + python tess_3_Params.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 = 732 Number of elements = 1781 Number of triangle elements = 1781 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 732 Total number of elements = 1781 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 934 Number of elements = 2228 Number of triangle elements = 2228 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 934 Total number of elements = 2228 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 3545 Number of elements = 7669 Number of triangle elements = 7669 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3545 Total number of elements = 7669 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m33.898s user 0m55.199s sys 2m35.436s + status=0 + set +x ================================================= data/session09/tess_3_Params.py passed (as expected) ================================================= ================================================= tess_4_Params.py test; + python tess_4_Params.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 = 1406 Number of elements = 3137 Number of triangle elements = 3137 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 1406 Total number of elements = 3137 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 2097 Number of elements = 4570 Number of triangle elements = 4570 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 2097 Total number of elements = 4570 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 6562 Number of elements = 13689 Number of triangle elements = 13689 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 6562 Total number of elements = 13689 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m33.789s user 0m56.986s sys 2m36.736s + status=0 + set +x ================================================= data/session09/tess_4_Params.py passed (as expected) ================================================= ================================================= tess_5_Params.py test; + python tess_5_Params.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 = 3537 Number of elements = 7415 Number of triangle elements = 7415 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3537 Total number of elements = 7415 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 12458 Number of elements = 25384 Number of triangle elements = 25384 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 12458 Total number of elements = 25384 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 45075 Number of elements = 90817 Number of triangle elements = 90817 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 45075 Total number of elements = 90817 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m35.325s user 1m3.637s sys 1m36.188s + status=0 + set +x ================================================= data/session09/tess_5_Params.py passed (as expected) ================================================= ================================================= tess_6_TriQuad.py test; + python tess_6_TriQuad.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 = 8302 Number of elements = 17191 Number of triangle elements = 17191 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 8302 Total number of elements = 17191 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 72029 Number of elements = 74322 Number of triangle elements = 0 Number of quadrilateral elements = 74322 ---------------------------- Total number of nodes = 72029 Total number of elements = 74322 ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m56.228s user 1m16.028s sys 2m6.893s + 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 /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 = 8302 Number of elements = 17191 Number of triangle elements = 17191 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 8302 Total number of elements = 17191 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - leadingEdge Mesh sizing name - rootLeadingEdge Done getting mesh sizing parameters Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 3919 Number of elements = 8410 Number of triangle elements = 8410 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 3919 Total number of elements = 8410 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = riteWingSkin, index = 3 Name = wingSpar1, index = 4 Name = leftWingSkin, index = 5 Name = wingTE, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting mesh sizing parameters Mesh sizing name - leadingEdge Mesh sizing name - rootLeadingEdge Done getting mesh sizing parameters Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 6181 Number of elements = 6607 Number of triangle elements = 0 Number of quadrilateral elements = 6607 ---------------------------- Total number of nodes = 6181 Total number of elements = 6607 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m34.925s user 0m56.515s sys 2m6.075s + status=0 + set +x ================================================= data/session09/tess_7_MeshSizing.py passed (as expected) ================================================= ================================================= tess_8_MeshSizing.py test; + python tess_8_MeshSizing.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 = 6587 Number of elements = 13200 Number of triangle elements = 13200 Number of quadrilateral elements = 0 ---------------------------- Total number of nodes = 6587 Total number of elements = 13200 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 5 Name = wingSpar2, index = 1 Name = wingRib, index = 2 Name = wingSpar1, index = 3 Name = leftWingSkin, index = 4 Name = riteWingSkin, index = 5 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = rootLeadingEdge, index = 3 Getting mesh sizing parameters Mesh sizing name - rootLeadingEdge Mesh sizing name - wingSpar1 Done getting mesh sizing parameters Getting surface mesh for body 1 (of 1) Body 1 (of 1) Number of nodes = 22190 Number of elements = 22191 Number of triangle elements = 0 Number of quadrilateral elements = 22191 ---------------------------- Total number of nodes = 22190 Total number of elements = 22191 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m37.517s user 0m58.136s sys 2m20.857s + status=0 + set +x ================================================= data/session09/tess_8_MeshSizing.py passed (as expected) ================================================= ================================================= tess_MinQuad.py test; + python tess_MinQuad.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../../data/ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m30.666s user 0m47.824s sys 2m31.229s + status=0 + set +x ================================================= solutions/session09/tess_MinQuad.py passed (as expected) ================================================= ================================================= tess_2k.py test; + python tess_2k.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../../data/ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m35.083s user 0m52.251s sys 2m42.051s + status=0 + set +x ================================================= solutions/session09/tess_2k.py passed (as expected) ================================================= ================================================= astros_1_ModalClamped.py test; + python astros_1_ModalClamped.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running ASTROS pre-analysis... ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 : 0.102451 3 : 0.102451 4 : 0.159637 5 : 0.159637 6 : 0.215446 7 : 0.215446 8 : 0.350115 9 : 0.350115 10: 0.466966 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m35.386s user 0m51.284s sys 2m8.301s + status=0 + set +x ================================================= data/session10/astros_1_ModalClamped.py passed (as expected) ================================================= ================================================= astros_2_ModalSupport.py test; + python astros_2_ModalSupport.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running ASTROS pre-analysis... ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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 : 0.0 2 : 0.0357647 3 : 0.0365801 4 : 0.102451 5 : 0.102453 6 : 0.159637 7 : 0.1611 8 : 0.215446 9 : 0.215462 10: 0.350115 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m34.535s user 0m51.512s sys 2m33.369s + status=0 + set +x ================================================= data/session10/astros_2_ModalSupport.py passed (as expected) ================================================= ================================================= astros_3_StaticClamped.py test; + python astros_3_StaticClamped.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running ASTROS pre-analysis... ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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... --> Maximum displacements: --> Tmax 43461.879162311016 --> T1max 738.595 --> T2max 3686.25 --> T3max 43363.8 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m34.323s user 0m50.857s sys 2m28.106s + status=0 + set +x ================================================= data/session10/astros_3_StaticClamped.py passed (as expected) ================================================= ================================================= astros_4_Composite.py test; + python astros_4_Composite.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running ASTROS pre-analysis... ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/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... --> Maximum displacements: --> Tmax 12131.654370141774 --> T1max 275.241 --> T2max 1005.74 --> T3max 12103.5 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m34.017s user 0m49.552s sys 2m6.938s + status=0 + set +x ================================================= data/session10/astros_4_Composite.py passed (as expected) ================================================= ================================================= nastran_5_Flutter.py test; + python nastran_5_Flutter.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log ==> Loading geometry from file "../ESP/wing3.csm"... Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running Nastran pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = Wing, index = 1 Name = wingSpar2, index = 2 Name = wingRib, index = 3 Name = riteWingSkin, index = 4 Name = wingSpar1, index = 5 Name = leftWingSkin, index = 6 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 4 Name = wingSpar2, index = 1 Name = wingSpar1, index = 2 Name = leadingEdge, index = 3 Name = rootLeadingEdge, index = 4 Getting surface mesh for body 1 (of 4) Getting surface mesh for body 2 (of 4) Getting surface mesh for body 3 (of 4) Getting surface mesh for body 4 (of 4) Body 1 (of 4) Number of nodes = 11 Number of elements = 6 Number of triangle elements = 0 Number of quadrilateral elements = 6 Body 2 (of 4) Number of nodes = 11 Number of elements = 6 Number of triangle elements = 0 Number of quadrilateral elements = 6 Body 3 (of 4) Number of nodes = 11 Number of elements = 6 Number of triangle elements = 0 Number of quadrilateral elements = 6 Body 4 (of 4) Number of nodes = 939 Number of elements = 1094 Number of triangle elements = 0 Number of quadrilateral elements = 1094 ---------------------------- Total number of nodes = 972 Total number of elements = 1112 Mapping Csys attributes ................ Number of unique Csys attributes = 2 Name = leftWingSkin, index = 1 Name = riteWingSkin, index = 2 Getting FEA coordinate systems....... Number of coordinate systems - 2 Coordinate system name - leftWingSkin Coordinate system name - riteWingSkin Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 1 Name = rootConstraint, index = 1 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 2 Name = ritePointLoad, index = 1 Name = leftPointLoad, index = 2 Mapping capsBound attributes ................ Number of unique capsBound attributes = 4 Name = upperWing, index = 1 Name = lowerWing, index = 2 Name = leftTip, index = 3 Name = riteTip, index = 4 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsResponse attributes ................ Number of unique capsResponse attributes = 0 Mapping capsReference attributes ................ Number of unique capsReference attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = Wing, index = 1 Name = wingSpar2, index = 2 Name = wingRib, index = 3 Name = riteWingSkin, index = 4 Name = wingSpar1, index = 5 Name = leftWingSkin, index = 6 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 11 Number of elements = 6 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 6 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 11 Number of elements = 6 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 6 Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 11 Number of elements = 6 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 6 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 939 Number of elements = 1094 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 1094 Combining multiple FEA meshes! Combined Number of nodal coordinates = 972 Combined Number of elements = 1112 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 1112 Getting vortex lattice surface data VLM surface name - upperWing Done getting vortex lattice surface data Getting FEA vortex lattice mesh Surface 1: Number of points found for aero-spline = 108 Surface 2: Number of points found for aero-spline = 108 Aero_Reference value is NULL - No aero reference parameters set Getting FEA materials....... Number of materials - 2 Material name - Madeupium Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 5 Property name - leftWingSkin Property name - riteWingSkin Property name - wingRib Property name - wingSpar1 Property name - wingSpar2 Done getting FEA properties Updating mesh element types based on properties input Getting FEA constraints....... Number of constraints - 1 Constraint name - rootConstraint No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement" No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name Done getting FEA constraints Support tuple is NULL - No supports applied Connect tuple is NULL - Using defaults Load tuple is NULL - No loads applied Design_Variable tuple is NULL - No design variables applied Design_Constraint tuple is NULL - No design constraints applied Design_Equation tuple is NULL - No design equations applied Design_Table tuple is NULL - No design table constants applied Design_Opt_Param tuple is NULL - No design optimization parameters applied Mass_Increment tuple is NULL - No mass increments applied Design_Response tuple is NULL - No design responses applied Design_Equation_Response tuple is NULL - No design equation responses applied Getting FEA analyses....... Number of analyses - 1 Analysis name - Flutter Done getting FEA analyses Writing Nastran grid and connectivity file (in large field format) .... Finished writing Nastran grid file Writing subElement types (if any) - appending mesh file Writing mass increment set Writing Nastran instruction file.... Warning: No loads specified for case Flutter!!!! Writing mass increment cards Writing aero card Writing analysis cards, 0 Writing constraint ADD cards Writing constraint cards Writing material cards Writing property cards Writing coordinate system cards Writing aeroelastic cards Done writing aeroelastic cards Done writing files ==> Running Nastran... sh: 1: nastran: not found Traceback (most recent call last): File "/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/data/session10/nastran_5_Flutter.py", line 138, in <module> nastran.postAnalysis() File "/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/problem.py", line 2159, in postAnalysis self._analysisObj.postAnalysis() File "/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed return func(*args, **kwargs) ^^^^^^^^^^^^^^^^^^^^^ File "/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 2913, in postAnalysis if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs)) ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^ File "/jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus raise CAPSError(status, msg=msg, errors=errors) pyCAPS.caps.CAPSError: CAPS_IOERR: ================================================================================ nastranAIM.c:3037 in aimPostAnalysis(): Error: Unable to open file: nastran_modal.f06 ================================================================================ ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m29.723s user 0m46.710s sys 2m7.850s + status=1 + set +x ================================================= data/session10/nastran_5_Flutter.py failed (as NOT expected) ================================================= ================================================= aeroelastic_2_Iterative_SU2_Astros.py test; + python aeroelastic_2_Iterative_SU2_Astros.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/training.log Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory Information: Dynamic Loader for scribeWake.so not found scribeWake.so: cannot open shared object file: No such file or directory ==> Running SU2 pre-analysis... Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = Wing, index = 1 Name = Farfield, index = 2 Mapping capsMesh attributes ................ Number of unique capsMesh attributes = 3 Name = leftWing, index = 1 Name = riteWing, index = 2 Name = Farfield, index = 3 Getting mesh sizing parameters Mesh sizing name - Farfield Mesh sizing name - leftWing Mesh sizing name - riteWing Done getting mesh sizing parameters AFLR2 : --------------------------------------- AFLR2 : AFLR2 LIBRARY AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION AFLR2 : TRIA/QUAD GRID GENERATOR AFLR2 : Version Number 9.14.7 AFLR2 : Version Date 07/16/23 @ 01:42PM AFLR2 : Compile OS Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR2 : Compile Date 07/25/23 @ 11:58AM 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR4 : Compile Date 08/14/23 @ 01:20PM 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 = 0.429 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR2 : Compile Date 07/25/23 @ 11:58AM 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR4 : Compile Date 08/14/23 @ 01:20PM 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 Linux 3.10.0-1160.88.1.el7.x86_64 x86_64 AFLR3 : Compile Date 07/26/23 @ 01:49PM 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 = 0.032 seconds AFLR3 IG : INITIAL VOLUME GRID GENERATION AFLR3 IG : Nodes, Elements = 9265 0 AFLR3 IG : Nodes, Elements = 8 10 AFLR3 IG : Nodes, Elements = 1854 12666 AFLR3 IG : Nodes, Elements = 3708 26130 AFLR3 IG : Nodes, Elements = 5562 39589 AFLR3 IG : Nodes, Elements = 7416 54244 AFLR3 IG : Nodes, Elements = 9270 69463 AFLR3 IG : Nodes, Elements = 9272 69530 AFLR3 IG : Nodes, Elements = 9272 69335 AFLR3 IG : Nodes, Elements = 9265 42285 AFLR3 IG : Nodes, Elements = 9265 42353 AFLR3 IG : Nodes, Elements = 9265 30496 AFLR3 IG : Nodes, Elements = 9265 28301 AFLR3 : CPU Time = 0.346 seconds AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION AFLR3 GG : Nodes, Elements = 9265 28301 AFLR3 GG : Nodes, Elements = 13542 41195 AFLR3 GG : Nodes, Elements = 13542 58908 AFLR3 GG : Nodes, Elements = 13542 54250 AFLR3 GG : Nodes, Elements = 17058 65245 AFLR3 GG : Nodes, Elements = 17058 78728 AFLR3 GG : Nodes, Elements = 17058 74303 AFLR3 GG : Nodes, Elements = 20605 85295 AFLR3 GG : Nodes, Elements = 20605 99195 AFLR3 GG : Nodes, Elements = 20605 94904 AFLR3 GG : Nodes, Elements = 24311 106150 AFLR3 GG : Nodes, Elements = 24311 121010 AFLR3 GG : Nodes, Elements = 24311 116688 AFLR3 GG : Nodes, Elements = 28109 128222 AFLR3 GG : Nodes, Elements = 28109 143116 AFLR3 GG : Nodes, Elements = 28109 139085 AFLR3 GG : Nodes, Elements = 31833 150343 AFLR3 GG : Nodes, Elements = 31833 164956 AFLR3 GG : Nodes, Elements = 31833 161115 AFLR3 GG : Nodes, Elements = 35425 171944 AFLR3 GG : Nodes, Elements = 35425 186053 AFLR3 GG : Nodes, Elements = 35425 182380 AFLR3 GG : Nodes, Elements = 38915 192902 AFLR3 GG : Nodes, Elements = 38915 206546 AFLR3 GG : Nodes, Elements = 38915 203031 AFLR3 GG : Nodes, Elements = 42279 213161 AFLR3 GG : Nodes, Elements = 42279 226492 AFLR3 GG : Nodes, Elements = 42279 223051 AFLR3 GG : Nodes, Elements = 45563 232931 AFLR3 GG : Nodes, Elements = 45563 245768 AFLR3 GG : Nodes, Elements = 45563 242514 AFLR3 GG : Nodes, Elements = 48695 251935 AFLR3 GG : Nodes, Elements = 48695 264207 AFLR3 GG : Nodes, Elements = 48695 261088 AFLR3 GG : Nodes, Elements = 51591 269788 AFLR3 GG : Nodes, Elements = 51591 281183 AFLR3 GG : Nodes, Elements = 51591 278253 AFLR3 GG : Nodes, Elements = 54386 286650 AFLR3 GG : Nodes, Elements = 54386 297696 AFLR3 GG : Nodes, Elements = 54386 294892 AFLR3 GG : Nodes, Elements = 57084 303004 AFLR3 GG : Nodes, Elements = 57084 313644 AFLR3 GG : Nodes, Elements = 57084 310937 AFLR3 GG : Nodes, Elements = 59614 318534 AFLR3 GG : Nodes, Elements = 59614 328459 AFLR3 GG : Nodes, Elements = 59614 326028 AFLR3 GG : Nodes, Elements = 61932 332987 AFLR3 GG : Nodes, Elements = 61932 342053 AFLR3 GG : Nodes, Elements = 61932 339758 AFLR3 GG : Nodes, Elements = 64173 346486 AFLR3 GG : Nodes, Elements = 64173 355203 AFLR3 GG : Nodes, Elements = 64173 353091 AFLR3 GG : Nodes, Elements = 66220 359236 AFLR3 GG : Nodes, Elements = 66220 367234 AFLR3 GG : Nodes, Elements = 66220 365224 AFLR3 GG : Nodes, Elements = 68183 371120 AFLR3 GG : Nodes, Elements = 68183 378771 AFLR3 GG : Nodes, Elements = 68183 376893 AFLR3 GG : Nodes, Elements = 70021 382413 AFLR3 GG : Nodes, Elements = 70021 389635 AFLR3 GG : Nodes, Elements = 70021 387894 AFLR3 GG : Nodes, Elements = 71738 393050 AFLR3 GG : Nodes, Elements = 71738 399670 AFLR3 GG : Nodes, Elements = 71738 398113 AFLR3 GG : Nodes, Elements = 73289 402770 AFLR3 GG : Nodes, Elements = 73289 408828 AFLR3 GG : Nodes, Elements = 73289 407358 AFLR3 GG : Nodes, Elements = 74785 411846 AFLR3 GG : Nodes, Elements = 74785 417552 AFLR3 GG : Nodes, Elements = 74785 416226 AFLR3 GG : Nodes, Elements = 76147 420314 AFLR3 GG : Nodes, Elements = 76147 425638 AFLR3 GG : Nodes, Elements = 76147 424379 AFLR3 GG : Nodes, Elements = 77386 428096 AFLR3 GG : Nodes, Elements = 77386 432940 AFLR3 GG : Nodes, Elements = 77386 431774 AFLR3 GG : Nodes, Elements = 78483 435067 AFLR3 GG : Nodes, Elements = 78483 439378 AFLR3 GG : Nodes, Elements = 78483 438266 AFLR3 GG : Nodes, Elements = 79434 441119 AFLR3 GG : Nodes, Elements = 79434 444842 AFLR3 GG : Nodes, Elements = 79434 443913 AFLR3 GG : Nodes, Elements = 80223 446281 AFLR3 GG : Nodes, Elements = 80223 449423 AFLR3 GG : Nodes, Elements = 80223 448600 AFLR3 GG : Nodes, Elements = 80840 450451 AFLR3 GG : Nodes, Elements = 80840 452964 AFLR3 GG : Nodes, Elements = 80840 452292 AFLR3 GG : Nodes, Elements = 81284 453624 AFLR3 GG : Nodes, Elements = 81284 455393 AFLR3 GG : Nodes, Elements = 81284 454894 AFLR3 GG : Nodes, Elements = 81599 455839 AFLR3 GG : Nodes, Elements = 81599 457118 AFLR3 GG : Nodes, Elements = 81599 456750 AFLR3 GG : Nodes, Elements = 81779 457290 AFLR3 GG : Nodes, Elements = 81779 458010 AFLR3 GG : Nodes, Elements = 81779 457813 AFLR3 GG : Nodes, Elements = 81888 458140 AFLR3 GG : Nodes, Elements = 81888 458622 AFLR3 GG : Nodes, Elements = 81888 458452 AFLR3 GG : Nodes, Elements = 81937 458599 AFLR3 GG : Nodes, Elements = 81937 458810 AFLR3 GG : Nodes, Elements = 81937 458739 AFLR3 GG : Nodes, Elements = 81953 458787 AFLR3 GG : Nodes, Elements = 81953 458858 AFLR3 GG : Nodes, Elements = 81953 458828 AFLR3 GG : Nodes, Elements = 81961 458852 AFLR3 GG : Nodes, Elements = 81961 458887 AFLR3 GG : Nodes, Elements = 81961 458871 AFLR3 GG : Nodes, Elements = 81966 458886 AFLR3 GG : Nodes, Elements = 81966 458898 AFLR3 GG : Nodes, Elements = 81966 458893 AFLR3 GG : Nodes, Elements = 81968 458899 AFLR3 GG : Nodes, Elements = 81968 458905 AFLR3 GG : Nodes, Elements = 81968 458903 AFLR3 : CPU Time = 5.386 seconds AFLR3 QI : QUALITY IMPROVEMENT AFLR3 QI : Nodes, Elements = 81968 458903 AFLR3 QI : Nodes, Elements = 81513 456317 AFLR3 QI : Nodes, Elements = 81426 455827 AFLR3 QI : Nodes, Elements = 81418 455777 AFLR3 QI : Nodes, Elements = 81416 455768 AFLR3 QI : Nodes, Elements = 81416 457723 AFLR3 QI : Nodes, Elements = 81416 455611 AFLR3 QI : Nodes, Elements = 81416 454711 AFLR3 QI : Nodes, Elements = 81416 454979 AFLR3 QI : Nodes, Elements = 81416 454537 AFLR3 QI : Nodes, Elements = 81416 454422 AFLR3 : CPU Time = 1.258 seconds AFLR3 : DONE UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 454422 UG3 : Min, Max Ang = 12.41 159.2 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 = 454422 UG3 : Min Vol = 1.01e-06 UG3 : Average Vol = 8.18 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 = 454422 UG3 : Min, Max Q = 0.205 1 UG3 : Average Q = 0.896 UG3 : No. Q< 0.1 = 0 UG3 : No. Q< 0.01 = 0 OVERALL : CPU Time = 7.211 seconds UG3 : DIHEDRAL ANGLE CHECK UG3 : No. Tet Elems = 454422 UG3 : Min, Max Ang = 12.41 159.2 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 = 454422 UG3 : Min Vol = 1.01e-06 UG3 : Average Vol = 8.18 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 = 454422 UG3 : Min, Max Q = 0.361 1 UG3 : Average Q = 0.863 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 = 81416 Number of elements = 472944 Number of triangles = 18522 Number of quadrilatarals = 0 Number of tetrahedrals = 454422 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...... /home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/io/config.py:142: ResourceWarning: unclosed file <_io.TextIOWrapper name='aeroelasticIterative.cfg' mode='r' encoding='UTF-8'> konfig = read_config(filename) ResourceWarning: Enable tracemalloc to get the object allocation traceback /home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/io/config.py:933: ResourceWarning: unclosed file <_io.TextIOWrapper name='config_CFD.cfg_tmp' mode='r' encoding='UTF-8'> for raw_line in open(temp_filename): ResourceWarning: Enable tracemalloc to get the object allocation traceback ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) 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. 81416 grid points. 454422 volume elements. 2 surface markers. 17886 boundary elements in index 0 (Marker = BC_1). 636 boundary elements in index 1 (Marker = BC_2). 454422 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: 49.4454. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 51.1523| 86.7063| | CV Face Area Aspect Ratio| 1.04012| 115.282| | CV Sub-Volume Ratio| 1| 701.712| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 81416| 1/1.00| 10| | 1| 13392| 1/6.08| 8.2187| | 2| 2069| 1/6.47| 6.61504| +-------------------------------------------+ 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| 3.4794e+00| -1.762880| 0.455100| 0.055818| 3.706226| -0.552238| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.3740e+00| -1.567620| 0.800265| 0.530357| 3.903824| -0.295493| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.3752e+00| -1.601362| 0.945584| 0.763508| 3.871421| 1.801614| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.3807e+00| -1.681553| 0.931856| 0.796718| 3.784455| -8.276542| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.3361e+00| -1.622632| 0.831000| 0.682309| 3.844421| -5.286333| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| -1.62263| < -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) ------------------------ /home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/run/interface.py:114: ResourceWarning: unclosed file <_io.BufferedReader name=4> run_command(the_Command) ResourceWarning: Enable tracemalloc to get the object allocation traceback ==> 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 = 6.247769e+09, tgt = 6.247769e+09, diff = 6.274147e-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 = 6.100462e+09, tgt = 6.100462e+09, diff = 2.016616e+00 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 = 6.121567e+07, tgt = 6.121567e+07, diff = 1.005828e-06 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 = 6.124703e+07, tgt = 6.124703e+07, diff = 1.490116e-08 Extracting external pressure loads from data transfer.... TransferName = upperWing Number of Elements = 96 (total = 96) Extracting external pressure loads from data transfer.... TransferName = lowerWing Number of Elements = 96 (total = 192) Extracting external pressure loads from data transfer.... TransferName = leftTip Number of Elements = 10 (total = 202) Extracting external pressure loads from data transfer.... TransferName = riteTip Number of Elements = 10 (total = 212) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Writing coordinate system cards Running mASTROS...... ==> Running ASTROS post-analysis... ==> 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...... /home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/io/config.py:933: ResourceWarning: unclosed file <_io.TextIOWrapper name='config_DEF.cfg_tmp' mode='r' encoding='UTF-8'> for raw_line in open(temp_filename): ResourceWarning: Enable tracemalloc to get the object allocation traceback ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) 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. 81416 grid points. 454422 volume elements. 2 surface markers. 17886 boundary elements in index 0 (Marker = BC_1). 636 boundary elements in index 1 (Marker = BC_2). 454422 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 26.084250 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) ------------------------ /home/jenkins/util/SU2/SU2-v8.0.0/bin/SU2/run/interface.py:136: ResourceWarning: unclosed file <_io.BufferedReader name=4> run_command(the_Command) ResourceWarning: Enable tracemalloc to get the object allocation traceback ------------------------------------------------------------------------- | ___ _ _ ___ | | / __| | | |_ ) 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. 81416 grid points. 454422 volume elements. 2 surface markers. 17886 boundary elements in index 0 (Marker = BC_1). 636 boundary elements in index 1 (Marker = BC_2). 454422 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 206540 TETRAHEDRON volume elements. There has been a re-orientation of 4612 TRIANGLE surface elements. Identifying edges and vertices. Setting the control volume structure. Volume of the computational grid: 1.43597e+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: 2.80094. Mean K: 0.00648824. Standard deviation K: 0.0460293. Checking for periodicity. Computing mesh quality statistics for the dual control volumes. +--------------------------------------------------------------+ | Mesh Quality Metric| Minimum| Maximum| +--------------------------------------------------------------+ | Orthogonality Angle (deg.)| 0.121691| 84.717| | CV Face Area Aspect Ratio| 1.95246| 1.70219e+06| | CV Sub-Volume Ratio| 1| 5.94835e+08| +--------------------------------------------------------------+ Setting the multigrid structure. +-------------------------------------------+ | MG Level| CVs|Aggl. Rate| CFL| +-------------------------------------------+ | 0| 81416| 1/1.00| 10| | 1| 13381| 1/6.08| 8.21645| | 2| 2059| 1/6.5| 6.60437| +-------------------------------------------+ Finding max control volume width. Semi-span length = 82551.9 m. Wetted area = 2.70595e+11 m^2. Area projection in the x-plane = 1.25588e+11 m^2, y-plane = 4.12513e+10 m^2, z-plane = 2.86662e+09 m^2. Max. coordinate in the x-direction = 3727.64 m, y-direction = 82551.9 m, z-direction = 0.130627 m. Min. coordinate in the x-direction = -24609 m, y-direction = -120594 m, z-direction = -1.48613e+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| 3.6015e+00| 11.159677| 14.127257| 14.015828| 16.628783| -0.042666| | 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.6360e+00| 11.301956| 14.039610| 13.927997| 16.736392| -0.029027| | 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.6005e+00| 11.448483| 14.102600| 13.975973| 16.875342| -0.037056| | 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.5783e+00| 11.512204| 14.155627| 14.033072| 16.942850| -0.026730| | 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.5840e+00| 11.589647| 14.217378| 14.110511| 17.004555| -0.046038| ----------------------------- Solver Exit ------------------------------- Maximum number of iterations reached (ITER = 5) before convergence. +-----------------------------------------------------------------------+ | Convergence Field | Value | Criterion | Converged | +-----------------------------------------------------------------------+ | rms[Rho]| 11.5896| < -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 3171 non-physical points in the solution. Warning: 929 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 = 3.497992e+09, tgt = 3.497992e+09, diff = 4.221015e+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 = 3.314377e+09, tgt = 3.314377e+09, diff = 3.628281e+00 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 = 1.512302e+07, tgt = 1.512302e+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 = 2.173615e+07, tgt = 2.173615e+07, diff = 8.428469e-04 Extracting external pressure loads from data transfer.... TransferName = upperWing Number of Elements = 96 (total = 96) Extracting external pressure loads from data transfer.... TransferName = lowerWing Number of Elements = 96 (total = 192) Extracting external pressure loads from data transfer.... TransferName = leftTip Number of Elements = 10 (total = 202) Extracting external pressure loads from data transfer.... TransferName = riteTip Number of Elements = 10 (total = 212) Writing Astros grid and connectivity file (in free field format) .... Finished writing Astros grid file Writing subElement types (if any) - appending mesh file Writing Astros instruction file.... Writing analysis cards Writing load ADD cards Writing constraint cards--each subcase individually Writing load cards Writing material cards Writing property cards Writing coordinate system cards Running mASTROS...... ==> Running ASTROS post-analysis... ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 5m24.419s user 4m22.058s sys 3m56.491s + status=0 + set +x ================================================= data/session11/aeroelastic_2_Iterative_SU2_Astros.py passed (as expected) ================================================= ************************************************* ************************************************* ================================================= Did not run examples for: session08 fun3d session11 fun3d+astros ================================================= ================================================= Summary of examples NOT finished as expected data/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/session07/pointwise_01_Defaults.py data/session07/pointwise_02_InviscidWing.py data/session07/pointwise_03_TurnAngle.py data/session07/pointwise_04_TurnAngleHard.py data/session07/pointwise_05_DomainDecay.py data/session07/pointwise_06_ConnectorProximity.py data/session07/pointwise_07_InviscidTransport.py data/session07/pointwise_08_ViscousWing.py solutions/session07/pointwise_DomainProximity.py data/session10/nastran_5_Flutter.py See training.log for more details. ================================================= Build step 'Execute shell' marked build as failure [GNU C Compiler (gcc)Clang] Skipping execution of recorder since overall result is 'FAILURE' [PostBuildScript] - [INFO] Executing post build scripts. [PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX [WS-CLEANUP] Deleting project workspace... [WS-CLEANUP] Skipped based on build state FAILURE Finished: FAILURE