The Jenkins Controller is preparing for shutdown. No new builds can be started.
Skipping 2,483 KB.. Full LogNumber of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing:faces, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input --> Mass = 14792888.88889 --> CG = [64.85254706407, 4.613994176513e-14, -3.914745293593] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m1.309s user 0m1.077s sys 0m0.587s + status=0 + set +x ================================================= data/session03/08_masstran_f118_Wing.py passed (as expected) ================================================= ================================================= 09_masstran_f118.py test; + python 09_masstran_f118.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "f118-C.csm"... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 6 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - Madeupium No "materialType" specified for Material tuple Madeupium, defaulting to "Isotropic" 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 - fuse:nose Property name - fuse:side Property name - fuse:tail Property name - htail:faces Property name - vtail:faces Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input -->Mass = 52825838.86801 -->CG = [91.69615213878, 9.02135549621e-15, 0.7254947287442] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m1.409s user 0m1.177s sys 0m0.611s + status=0 + set +x ================================================= data/session03/09_masstran_f118.py passed (as expected) ================================================= ================================================= 10_masstran_f118_journal.py test; + python 10_masstran_f118_journal.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ################################################################################ ==> First execution ==> Loading geometry from file "f118-C.csm"... ================================================================================ ==> Computing mass 1 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing:faces, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 488 Number of elements = 972 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 972 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input --> 14792888.88889 Something went wrong! ################################################################################ ==> Second execution ==> Loading geometry from file "f118-C.csm"... ================================================================================ ==> Computing mass 1 --> 14792888.88889 CAPS Info: Hit last success -- going live! ================================================================================ ==> Computing mass 2 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing:faces, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 488 Number of elements = 972 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 972 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input --> 1479288.888889 Something went wrong! ################################################################################ ==> Third execution ==> Loading geometry from file "f118-C.csm"... ================================================================================ ==> Computing mass 1 --> 14792888.88889 ================================================================================ ==> Computing mass 2 --> 1479288.888889 CAPS Info: Hit last success -- going live! ================================================================================ ==> Computing mass 3 Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wing:faces, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 488 Number of elements = 972 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 972 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input --> 147928.8888889 ################################################################################ ==> Fourth execution ==> Loading geometry from file "f118-C.csm"... ================================================================================ ==> Computing mass 1 --> 14792888.88889 ================================================================================ ==> Computing mass 2 --> 1479288.888889 ================================================================================ ==> Computing mass 3 --> 147928.8888889 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m1.657s user 0m1.257s sys 0m0.764s + status=0 + set +x ================================================= data/session03/10_masstran_f118_journal.py passed (as expected) ================================================= ================================================= + echo 'f118-C.csm test;' + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log f118-C.csm test; + /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/ESP/LINUX64/bin/serveESP -batch -verify -outLevel 0 f118-C.csm + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.7.0/f118-C.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.172s user 0m0.140s sys 0m0.094s + status=0 + set +x ================================================= solutions/session03/f118-C passed (as expected) ================================================= ================================================= xfoil_thickness.py test; + python xfoil_thickness.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/session03/naca.csm"... ==> Create xfoilAIM ==> Setting analysis values ==> Retrieve analysis results ==> Retrieve analysis results ==> Retrieve analysis results ==> Retrieve analysis results --> Thickness = [0.08, 0.1, 0.12, 0.16] --> Alpha = [[0.0, 1.0, 3.0], [0.0, 1.0, 3.0], [0.0, 1.0, 3.0], [0.0, 1.0, 3.0]] --> Cl = [[4.33419564648744e-07, 0.118003705247236, 0.407823091300475], [3.88197189072075e-07, 0.12399312361342, 0.371340021267193], [-3.53757498051076e-07, 0.126697477361204, 0.377437462181212], [-2.73508077086116e-07, 0.127624902798199, 0.380867789439149]] --> Cd = [[0.00449613835213466, 0.00482192214519439, 0.00769709940290313], [0.00540044826496244, 0.00554773736538666, 0.00718424709040524], [0.00617285380994943, 0.00627268560115553, 0.00729426778763046], [0.00752780925540312, 0.00759373202201068, 0.00822814692466907]] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m3.626s user 0m3.159s sys 0m0.813s + status=0 + set +x ================================================= solutions/session03/xfoil_thickness.py passed (as expected) ================================================= ================================================= f118_masstran.py test; + python f118_masstran.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/session03/f118-B.csm"... ==> Geometry with capsIntent=['wing','fuse', 'htail'] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m1.251s user 0m1.106s sys 0m0.491s + status=0 + set +x ================================================= solutions/session03/f118_masstran.py passed (as expected) ================================================= ================================================= masstran_topbot.py test; + python masstran_topbot.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "f118-C.csm"... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - Madeupium No "materialType" specified for Material tuple Madeupium, defaulting to "Isotropic" Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 8 Property name - fuse:bottom Property name - fuse:nose Property name - fuse:side Property name - fuse:tail Property name - fuse:top Property name - htail:faces Property name - vtail:faces Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input -->Mass = 52073438.86801 -->CG = [91.72065954403, 0.04009689171826, 0.1932821772294] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m1.368s user 0m1.157s sys 0m0.599s + status=0 + set +x ================================================= solutions/session03/masstran_topbot.py passed (as expected) ================================================= ================================================= masstran_CG.py test; + python masstran_CG.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "f118-C.csm"... Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 2 Material name - Madeupium No "materialType" specified for Material tuple Madeupium, defaulting to "Isotropic" Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 8 Property name - fuse:bottom Property name - fuse:nose Property name - fuse:side Property name - fuse:tail Property name - fuse:top Property name - htail:faces Property name - vtail:faces Property name - wing:faces Done getting FEA properties Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 8 Name = wing:faces, index = 1 Name = htail:faces, index = 2 Name = vtail:faces, index = 3 Name = fuse:nose, index = 4 Name = fuse:tail, index = 5 Name = fuse:side, index = 6 Name = fuse:bottom, index = 7 Name = fuse:top, index = 8 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 900 Number of elements = 1796 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 1796 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 170 Number of elements = 336 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 336 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 90 Number of elements = 176 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 176 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 1698 Number of elements = 3392 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 3392 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 2858 Combined Number of elements = 5700 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 5700 Combined Elemental Quad4 = 0 Updating mesh element types based on properties input -->Oringal CG = 91.72065954403 -->CG sweep = [84.05056882825, 85.58458697141, 87.11860511456, 88.65262325772, 90.18664140087, 91.72065954403, 93.25467768718, 94.78869583034, 96.32271397349, 97.85673211665, 99.3907502598] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m2.691s user 0m2.172s sys 0m1.132s + status=0 + set +x ================================================= solutions/session03/masstran_CG.py passed (as expected) ================================================= ================================================= + echo 'f118-D.csm test;' + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log f118-D.csm test; + /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/ESP/LINUX64/bin/serveESP -batch -verify -outLevel 0 f118-D.csm + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.7.0/f118-D.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.168s user 0m0.122s sys 0m0.106s + status=0 + set +x ================================================= data/session04/f118-D passed (as expected) ================================================= ================================================= + echo 'naca.csm test;' + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log naca.csm test; + /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/ESP/LINUX64/bin/serveESP -batch -verify -outLevel 0 naca.csm + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.7.0/naca.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.179s user 0m0.146s sys 0m0.053s + status=0 + set +x ================================================= data/session04/naca passed (as expected) ================================================= ================================================= 1_mses_Deriv.py test; + python 1_mses_Deriv.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "naca.csm"... ==> Area and Area derivatives... --> Area 0.08221896898506198 --> dArea/dthick 0.6847211877073471 ==> Drag and Drag derivatives... Getting CFD design variables....... Number of design variables - 2 Design Variable name - camber Design Variable name - thick Done getting CFD design variables --> CD = 0.005288407957828104 --> dCD/dAlpha = -2.872248609495725e-07 --> dCD/dMach = 0.001245336656748457 --> dCD/dcamber = -3.202100499013558e-05 --> dCD/dthick = 0.015720668390468186 ==> All Drag derivatives... --> CD derivs = {'Alpha': -2.872248609495725e-07, 'Mach': 0.001245336656748457, 'Re': -3.63877256438553e-11, 'camber': -3.202100499013558e-05, 'thick': 0.015720668390468186} ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m5.008s user 0m4.707s sys 0m0.656s + status=0 + set +x ================================================= data/session04/1_mses_Deriv.py passed (as expected) ================================================= ================================================= 3_mses_OpenMDAO_CD_Alpha.py test; + python 3_mses_OpenMDAO_CD_Alpha.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Starting Optimization... --> Alpha [3.] --> CD [0.00803595] --> Alpha [3.] --> CD [0.00803595] --> Alpha [3.] --> CD_alpha [[0.00014124]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 1 M = 10 At X0 0 variables are exactly at the bounds At iterate 0 f= 8.03595D-03 |proj g|= 1.41235D-04 --> Alpha [2.99985876] --> CD [0.00803593] --> Alpha [2.99985876] --> CD_alpha [[0.00014123]] At iterate 1 f= 8.03593D-03 |proj g|= 1.41231D-04 --> Alpha [-1.95854356] --> CD [0.0079199] --> Alpha [-1.95854356] --> CD_alpha [[-8.82232953e-05]] At iterate 2 f= 7.91990D-03 |proj g|= 8.82233D-05 --> Alpha [-0.05208097] --> CD [0.00783467] --> Alpha [-0.05208097] --> CD_alpha [[-2.58066343e-06]] At iterate 3 f= 7.83467D-03 |proj g|= 2.58066D-06 --> Alpha [0.00536633] --> CD [0.0078346] --> Alpha [0.00536633] --> CD_alpha [[1.70845241e-08]] At iterate 4 f= 7.83460D-03 |proj g|= 1.70845D-08 --> Alpha [0.00498852] --> CD [0.0078346] --> Alpha [0.00498852] --> CD_alpha [[-1.98581268e-09]] At iterate 5 f= 7.83460D-03 |proj g|= 1.98581D-09 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 1 5 6 5 0 0 1.986D-09 7.835D-03 F = 7.8346014606118335E-003 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- --> Optimized value: [0.00498852] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* 102 9208 *scipy* ----------------------------------------------------- real 0m28.386s user 0m27.733s sys 0m1.560s + status=0 + set +x ================================================= data/session04/3_mses_OpenMDAO_CD_Alpha.py passed (as expected) ================================================= ================================================= 5_mses_OpenMDAO_CD_camber.py test; + python 5_mses_OpenMDAO_CD_camber.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Starting Optimization... --> camber [0.1] Getting CFD design variables....... Number of design variables - 1 Design Variable name - camber Done getting CFD design variables --> CD [0.01370215] --> camber [0.1] --> CD [0.01370215] --> camber [1.1] ================================================================= ==3078953==ERROR: AddressSanitizer: heap-buffer-overflow on address 0x61b000628bc8 at pc 0x7fe290698c2b bp 0x7ffe1e197fe0 sp 0x7ffe1e197fd0 WRITE of size 8 at 0x61b000628bc8 thread T0 #0 0x7fe290698c2a in vlm_getSectionCoord /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/aim/utils/vlmUtils.c:3131 #1 0x7fe290641877 in aimUpdateState /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/aim/mses/msesAIM.c:757 #2 0x7fe2acb435e3 in aim_UpdateState /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsAIM.c:446 #3 0x7fe2acb2efa7 in caps_updateState /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsAnalysis.c:4147 #4 0x7fe2acb2f3b4 in caps_preAnalysiX 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_PyEval_EvalFrameDefault Python/ceval.c:5376 #95 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73 #96 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434 #97 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393 #98 0x7fe2b72f2817 in _PyObject_VectorcallTstate Include/internal/pycore_call.h:92 #99 0x7fe2b72f2817 in method_vectorcall Objects/classobject.c:67 #100 0x7fe2b72e8c6c in _PyVectorcall_Call Objects/call.c:245 #101 0x7fe2b72e973c in _PyObject_Call Objects/call.c:328 #102 0x7fe2b72e9861 in PyObject_Call Objects/call.c:355 #103 0x7fe2b7574663 in do_call_core Python/ceval.c:7349 #104 0x7fe2b75a76eb in _PyEval_EvalFrameDefault Python/ceval.c:5376 #105 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73 #106 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434 #107 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393 #108 0x7fe2b72eaa3d in _PyObject_FastCallDictTstate Objects/call.c:141 #109 0x7fe2b72eb1ca in _PyObject_Call_Prepend Objects/call.c:482 #110 0x7fe2b74233b9 in slot_tp_call Objects/typeobject.c:7624 #111 0x7fe2b72e9d75 in _PyObject_MakeTpCall Objects/call.c:214 #112 0x7fe2b72ea409 in _PyObject_VectorcallTstate Include/internal/pycore_call.h:90 #113 0x7fe2b72ea499 in PyObject_Vectorcall Objects/call.c:299 #114 0x7fe2b759f454 in _PyEval_EvalFrameDefault Python/ceval.c:4769 #115 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73 #116 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434 #117 0x7fe2b75ac41f in PyEval_EvalCode Python/ceval.c:1148 #118 0x7fe2b7664f6c in run_eval_code_obj Python/pythonrun.c:1741 #119 0x7fe2b7665ee3 in run_mod Python/pythonrun.c:1762 #120 0x7fe2b7666097 in pyrun_file Python/pythonrun.c:1657 #121 0x7fe2b766db77 in _PyRun_SimpleFileObject Python/pythonrun.c:440 #122 0x7fe2b766de9f in _PyRun_AnyFileObject Python/pythonrun.c:79 #123 0x7fe2b76bf2b0 in pymain_run_file_obj Modules/main.c:360 #124 0x7fe2b76bfa90 in pymain_run_file Modules/main.c:379 #125 0x7fe2b76c2301 in pymain_run_python Modules/main.c:601 #126 0x7fe2b76c2484 in Py_RunMain Modules/main.c:680 #127 0x7fe2b76c267a in pymain_main Modules/main.c:710 #128 0x7fe2b76c29f8 in Py_BytesMain Modules/main.c:734 #129 0x55d6d316b195 in main Programs/python.c:15 #130 0x7fe2b6a29d8f in __libc_start_call_main ../sysdeps/nptl/libc_start_call_main.h:58 #131 0x7fe2b6a29e3f in __libc_start_main_impl ../csu/libc-start.c:392 #132 0x55d6d316b0c4 in _start (/home/jenkins/util/python/Python-3.11.9_address/install/bin/python3.11+0x10c4) 0x61b000628bc8 is located 0 bytes to the right of 1608-byte region [0x61b000628580,0x61b000628bc8) allocated by thread T0 here: #0 0x7fe2b7eb4887 in __interceptor_malloc ../../../../src/libsanitizer/asan/asan_malloc_linux.cpp:145 #1 0x7fe2b2332832 in EG_alloc /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/EGADS/trunk/src/egadsMemory.c:23 #2 0x7fe290697011 in vlm_getSectionCoord /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/aim/utils/vlmUtils.c:3058 #3 0x7fe290641877 in aimUpdateState /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/aim/mses/msesAIM.c:757 #4 0x7fe2acb435e3 in aim_UpdateState /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsAIM.c:446 #5 0x7fe2acb2efa7 in caps_updateState /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsAnalysis.c:4147 #6 0x7fe2acb2f3b4 in caps_preAnalysiX /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsAnalysis.c:4201 #7 0x7fe2acb359b0 in caps_execX /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsAnalysis.c:5088 #8 0x7fe2acba2b9f in caps_updateAnalysisOut /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsValue.c:274 #9 0x7fe2acba45cd in caps_getValuX /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsValue.c:409 #10 0x7fe2acba5687 in caps_getValue /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsValue.c:533 #11 0x7fe2b3e08e2d (/lib/x86_64-linux-gnu/libffi.so.8+0x7e2d) #12 0x7ffe1e19fc1f ([stack]+0x4cc1f) SUMMARY: AddressSanitizer: heap-buffer-overflow /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/aim/utils/vlmUtils.c:3131 in vlm_getSectionCoord Shadow bytes around the buggy address: 0x0c36800bd120: 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 0x0c36800bd130: 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 0x0c36800bd140: 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 0x0c36800bd150: 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 0x0c36800bd160: 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 =>0x0c36800bd170: 00 00 00 00 00 00 00 00 00[fa]fa fa fa fa fa fa 0x0c36800bd180: fa fa fa fa fa fa fa fa fa fa fa fa fa fa fa fa 0x0c36800bd190: 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 0x0c36800bd1a0: 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 0x0c36800bd1b0: 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 0x0c36800bd1c0: 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 00 Shadow byte legend (one shadow byte represents 8 application bytes): Addressable: 00 Partially addressable: 01 02 03 04 05 06 07 Heap left redzone: fa Freed heap region: fd Stack left redzone: f1 Stack mid redzone: f2 Stack right redzone: f3 Stack after return: f5 Stack use after scope: f8 Global redzone: f9 Global init order: f6 Poisoned by user: f7 Container overflow: fc Array cookie: ac Intra object redzone: bb ASan internal: fe Left alloca redzone: ca Right alloca redzone: cb Shadow gap: cc ==3078953==ABORTING real 0m10.480s user 0m10.095s sys 0m1.071s + status=1 + set +x ================================================= data/session04/5_mses_OpenMDAO_CD_camber.py failed (as NOT expected) ================================================= ================================================= 7_mses_OpenMDAO_CL2_camber.py test; + python 7_mses_OpenMDAO_CL2_camber.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log Traceback (most recent call last): File "/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/data/session04/7_mses_OpenMDAO_CL2_camber.py", line 78, in <module> capsProblem = pyCAPS.Problem(problemName="design_mses", ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^ File "/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/problem.py", line 449, in __init__ problemObj = caps.open(problemName, phaseName, flag, ptr, outLevel) ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^ File "/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 1123, in open _raiseStatus(stat, msg=msg, errors=capsErrs(nErr, errs)) File "/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus raise CAPSError(status, msg=msg, errors=errors) pyCAPS.caps.CAPSError: CAPS_DIRERR: Failed to open Problem with prName='design_mses', phName=None, flag=0, and ptr='naca.csm': ================================================================================ Lock file exists (caps_open)! If you believe that no one else is running here remove: /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/data/session04/design_mses/Scratch/capsLock ================================================================================ ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* 102 9208 *scipy* ----------------------------------------------------- real 0m5.683s user 0m5.564s sys 0m0.797s + status=1 + set +x ================================================= data/session04/7_mses_OpenMDAO_CL2_camber.py failed (as NOT expected) ================================================= ================================================= 8_mses_OpenMDAO_CDCL.py test; + python 8_mses_OpenMDAO_CDCL.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log Traceback (most recent call last): File "/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/data/session04/8_mses_OpenMDAO_CDCL.py", line 98, in <module> capsProblem = pyCAPS.Problem(problemName="design_mses", ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^ File "/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/problem.py", line 449, in __init__ problemObj = caps.open(problemName, phaseName, flag, ptr, outLevel) ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^ File "/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 1123, in open _raiseStatus(stat, msg=msg, errors=capsErrs(nErr, errs)) File "/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus raise CAPSError(status, msg=msg, errors=errors) pyCAPS.caps.CAPSError: CAPS_DIRERR: Failed to open Problem with prName='design_mses', phName=None, flag=0, and ptr='naca.csm': ================================================================================ Lock file exists (caps_open)! If you believe that no one else is running here remove: /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/data/session04/design_mses/Scratch/capsLock ================================================================================ ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* 102 9208 *scipy* ----------------------------------------------------- real 0m5.330s user 0m5.315s sys 0m0.696s + status=1 + set +x ================================================= data/session04/8_mses_OpenMDAO_CDCL.py failed (as NOT expected) ================================================= ================================================= 9_masstran_OpenMDAO_thick.py test; + python 9_masstran_OpenMDAO_thick.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Starting Optimization... /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/ESP/venv/lib/python3.11/site-packages/openmdao/core/driver.py:619: DriverWarning:The following design variable initial conditions are out of their specified bounds: masstranSystem.x2 val: [0.] lower: 0.01 upper: 10.0 Set the initial value of the design variable to a valid value or set the driver option['invalid_desvar_behavior'] to 'ignore'. --> x1 [0.1] --> x2 [0.] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuse Property name - htail Property name - vtail Property name - wing Done getting FEA properties Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [2.75695334] --> x1 [0.1] --> x2 [0.01] /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/data/session04/9_masstran_OpenMDAO_thick.py:52: DeprecationWarning: Conversion of an array with ndim > 0 to a scalar is deprecated, and will error in future. Ensure you extract a single element from your array before performing this operation. (Deprecated NumPy 1.25.) "x1": {"initialValue":float(inputs['x1'])}, /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/data/session04/9_masstran_OpenMDAO_thick.py:53: DeprecationWarning: Conversion of an array with ndim > 0 to a scalar is deprecated, and will error in future. Ensure you extract a single element from your array before performing this operation. (Deprecated NumPy 1.25.) "x2": {"initialValue":float(inputs['x2'])}, Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [2.70119648] --> x1 [0.1] --> x2 [0.01] --> dCGx_x1 [[-68.82272937]] --> dCGx_x2 [[-5.53091882]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 2 M = 10 At X0 1 variables are exactly at the bounds At iterate 0 f= 2.70120D+00 |proj g|= 9.90000D+00 --> x1 [10.] --> x2 [5.54091882] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [10.16370853] --> x1 [10.] --> x2 [5.54091882] --> dCGx_x1 [[0.04843981]] --> dCGx_x2 [[0.03754845]] --> x1 [3.33378327] --> x2 [1.81664573] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [8.85443326] --> x1 [3.33378327] --> x2 [1.81664573] --> dCGx_x1 [[0.48418692]] --> dCGx_x2 [[0.1268106]] --> x1 [1.12760341] --> x2 [0.5841001] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [5.7972651] --> x1 [1.12760341] --> x2 [0.5841001] --> dCGx_x1 [[3.182136]] --> dCGx_x2 [[0.42790152]] --> x1 [0.42334159] --> x2 [0.19064405] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [1.60230885] --> x1 [0.42334159] --> x2 [0.19064405] --> dCGx_x1 [[8.88674345]] --> dCGx_x2 [[0.86253194]] At iterate 1 f= 1.60231D+00 |proj g|= 4.13342D-01 --> x1 [0.38612876] --> x2 [0.16914154] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [1.24954556] --> x1 [0.38612876] --> x2 [0.16914154] --> dCGx_x1 [[9.04121089]] --> dCGx_x2 [[0.8599867]] --> x1 [0.23727742] --> x2 [0.08313149] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [0.04927766] --> x1 [0.23727742] --> x2 [0.08313149] --> dCGx_x1 [[3.58807069]] --> dCGx_x2 [[0.31359947]] At iterate 2 f= 4.92777D-02 |proj g|= 2.27277D-01 --> x1 [0.11213433] --> x2 [0.01347811] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [1.95060563] --> x1 [0.11213433] --> x2 [0.01347811] --> dCGx_x1 [[-52.76118222]] --> dCGx_x2 [[-4.27221829]] --> x1 [0.21361795] --> x2 [0.06996287] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [5.61440048e-05] --> x1 [0.21361795] --> x2 [0.06996287] --> dCGx_x1 [[0.13868009]] --> dCGx_x2 [[0.01195172]] At iterate 3 f= 5.61440D-05 |proj g|= 1.38680D-01 --> x1 [0.21266725] --> x2 [0.06943529] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [3.06804662e-06] --> x1 [0.21266725] --> x2 [0.06943529] --> dCGx_x1 [[-0.03260179]] --> dCGx_x2 [[-0.00280809]] At iterate 4 f= 3.06805D-06 |proj g|= 3.26018D-02 --> x1 [0.2128482] --> x2 [0.0695357] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [1.43517333e-10] --> x1 [0.2128482] --> x2 [0.0695357] --> dCGx_x1 [[0.00022274]] --> dCGx_x2 [[1.91872562e-05]] At iterate 5 f= 1.43517D-10 |proj g|= 2.22739D-04 --> x1 [0.21284697] --> x2 [0.06953502] Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - x1 Design_Variable name - x2 Design_Variable_Relation name - fuseRel Design_Variable_Relation name - wingRel Number of design variable relations - 2 Done getting FEA design variables --> dCGx [3.63550505e-16] --> x1 [0.21284697] --> x2 [0.06953502] --> dCGx_x1 [[3.54510824e-07]] --> dCGx_x2 [[3.05383747e-08]] At iterate 6 f= 3.63551D-16 |proj g|= 3.54511D-07 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 2 6 12 7 0 0 3.545D-07 3.636D-16 F = 3.6355050512987024E-016 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- ==> Optimized value: --> x1 [0.21284697] --> x2 [0.06953502] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* 102 9208 *scipy* ----------------------------------------------------- real 0m8.153s user 0m7.354s sys 0m1.963s + status=0 + set +x ================================================= data/session04/9_masstran_OpenMDAO_thick.py passed (as expected) ================================================= ================================================= masstran_OpenMDAO_geom.py test; + python masstran_OpenMDAO_geom.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Initial values: htail:lh 5.0 wing:xroot 4.0 ==> Starting Optimization... --> htail:lh [5.] --> wing:xroot [4.] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Getting FEA materials....... Number of materials - 2 Material name - madeupium Material name - unobtainium Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuse Property name - htail Property name - vtail Property name - wing Done getting FEA properties Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [2.10539929] --> htail:lh [5.] --> wing:xroot [4.] --> dCGx [2.10539929] --> htail:lh [5.] --> wing:xroot [4.] --> dCGx_htail:lh [[-0.40374365]] --> dCGx_wing:xroot [[-1.15229479]] RUNNING THE L-BFGS-B CODE * * * Machine precision = 2.220D-16 N = 2 M = 10 At X0 0 variables are exactly at the bounds At iterate 0 f= 2.10540D+00 |proj g|= 1.15229D+00 --> htail:lh [5.40374365] --> wing:xroot [5.15229479] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [0.86918465] --> htail:lh [5.40374365] --> wing:xroot [5.15229479] --> dCGx_htail:lh [[-0.30002756]] --> dCGx_wing:xroot [[-0.74124931]] At iterate 1 f= 8.69185D-01 |proj g|= 7.41249D-01 --> htail:lh [6.474753] --> wing:xroot [7.25471671] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [0.00905292] --> htail:lh [6.474753] --> wing:xroot [7.25471671] --> dCGx_htail:lh [[0.03711399]] --> dCGx_wing:xroot [[0.07531706]] At iterate 2 f= 9.05292D-03 |proj g|= 7.53171D-02 --> htail:lh [6.35917671] --> wing:xroot [7.05983716] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [1.94377289e-05] --> htail:lh [6.35917671] --> wing:xroot [7.05983716] --> dCGx_htail:lh [[-0.00169617]] --> dCGx_wing:xroot [[-0.00349307]] At iterate 3 f= 1.94377D-05 |proj g|= 3.49307D-03 --> htail:lh [6.3642348] --> wing:xroot [7.06847132] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [2.31615861e-10] --> htail:lh [6.3642348] --> wing:xroot [7.06847132] --> dCGx_htail:lh [[-5.85873617e-06]] --> dCGx_wing:xroot [[-1.20573655e-05]] At iterate 4 f= 2.31616D-10 |proj g|= 1.20574D-05 --> htail:lh [6.36425233] --> wing:xroot [7.06850123] Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wing, index = 1 Name = htail, index = 2 Name = vtail, index = 3 Name = fuse, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2168 Number of elements = 2166 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 0 Elemental Quad4 = 2166 Combining multiple FEA meshes! Combined Number of nodal coordinates = 8672 Combined Number of elements = 8664 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 0 Combined Elemental Quad4 = 8664 Updating mesh element types based on properties input Getting FEA design variables....... Number of design variables - 2 Design_Variable name - htail:lh Design_Variable name - wing:xroot Number of design variable relations - 0 Done getting FEA design variables --> dCGx [6.3756283e-18] --> htail:lh [6.36425233] --> wing:xroot [7.06850123] --> dCGx_htail:lh [[9.72035735e-10]] --> dCGx_wing:xroot [[2.00045928e-09]] At iterate 5 f= 6.37563D-18 |proj g|= 2.00046D-09 * * * Tit = total number of iterations Tnf = total number of function evaluations Tnint = total number of segments explored during Cauchy searches Skip = number of BFGS updates skipped Nact = number of active bounds at final generalized Cauchy point Projg = norm of the final projected gradient F = final function value * * * N Tit Tnf Tnint Skip Nact Projg F 2 5 6 5 0 0 2.000D-09 6.376D-18 F = 6.3756282976940919E-018 CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH Optimization Complete ----------------------------------- ==> Optimized values: --> htail:lh 6.364252334270465 --> wing:xroot 7.06850122864588 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* 102 9208 *scipy* ----------------------------------------------------- real 0m9.632s user 0m8.882s sys 0m2.027s + status=0 + set +x ================================================= solutions/session04/masstran_OpenMDAO_geom.py passed (as expected) ================================================= ================================================= + echo 'avlPlaneVanilla.csm test;' + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log avlPlaneVanilla.csm test; + /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/ESP/LINUX64/bin/serveESP -batch -verify -outLevel 0 avlPlaneVanilla.csm + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log WARNING:: cannot open "./verify_7.7.0/avlPlaneVanilla.vfy", so verification is being skipped ==> serveESP completed successfully with no verification data real 0m0.706s user 0m0.655s sys 0m0.121s + status=0 + set +x ================================================= data/session06/avlPlaneVanilla passed (as expected) ================================================= ================================================= 1_avl_PlaneVanilla.py test; + python 1_avl_PlaneVanilla.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "avlPlaneVanilla.csm"... ==> Viewing Plane Vanilla bodies... ==> Create avlAIM ==> Viewing AVL Plane Vanilla bodies... ==> Setting analysis values Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Warning: Control Elevator not found in controls tuple! Only defaults will be used. Warning: Control Elevator not found in controls tuple! Only defaults will be used. Warning: Control Elevator not found in controls tuple! Only defaults will be used. Warning: Control Rudder not found in controls tuple! Only defaults will be used. Warning: Control Rudder not found in controls tuple! Only defaults will be used. Warning: Control AileronRight not found in controls tuple! Only defaults will be used. Warning: Control AileronLeft not found in controls tuple! Only defaults will be used. Warning: Control AileronRight not found in controls tuple! Only defaults will be used. Warning: Control AileronLeft not found in controls tuple! Only defaults will be used. Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 1) Control surface 1 of 1 Section 2 of 3 (ID = 0) Control surface 1 of 1 Section 3 of 3 (ID = 2) Control surface 1 of 1 Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Control surface 1 of 1 Section 2 of 2 (ID = 0) Control surface 1 of 1 Writing surface - Wing (ID = 2) Section 1 of 3 (ID = 1) Control surface 1 of 1 Section 2 of 3 (ID = 0) Control surface 1 of 2 Control surface 2 of 2 Section 3 of 3 (ID = 2) Control surface 1 of 1 --> CLtot = 0.58136120092054 --> CDtot = 0.006414738598475671 --> CDind = 0.006414738598475671 --> e = 0.915541714504936 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m3.248s user 0m2.456s sys 0m1.121s + status=0 + set +x ================================================= data/session06/1_avl_PlaneVanilla.py passed (as expected) ================================================= ================================================= 2_avl_PlaneVanillaControl.py test; + python 2_avl_PlaneVanillaControl.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "avlPlaneVanilla.csm"... ==> Creating avlAIM ==> Setting analysis values ==> Some stability derivatives (old) Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice control surface data VLM control surface name - AileronLeft VLM control surface name - AileronRight VLM control surface name - Elevator VLM control surface name - Rudder Done getting vortex lattice control surface data Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 1) Control surface 1 of 1 Section 2 of 3 (ID = 0) Control surface 1 of 1 Section 3 of 3 (ID = 2) Control surface 1 of 1 Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Control surface 1 of 1 Section 2 of 2 (ID = 0) Control surface 1 of 1 Writing surface - Wing (ID = 2) Section 1 of 3 (ID = 1) Control surface 1 of 1 Section 2 of 3 (ID = 0) Control surface 1 of 2 Control surface 2 of 2 Section 3 of 3 (ID = 2) Control surface 1 of 1 --> CLa = 6.186807004021976 --> CLb = 0.06076552938630597 --> CLp' = 0.077268842659423 --> CLq' = 11.77186898080718 --> CLr' = 0.9883703770759704 --> dCL/dAileronRight = 0.02247452142329 --> dCL/dAileronLeft = 0.02252467496204 --> dCL/dElevator = 0.005432144424886 --> dCL/dRudder = -2.654020388411e-06 ==> Some stability derivatives (new) --> dCL/dAlpha = 6.186807004021976 --> dCL/dBeta = 0.06076552938630597 --> dCL/dp' = 0.077268842659423 --> dCL/dq' = 11.77186898080718 --> dCL/dr' = 0.9883703770759704 --> dCL/dAileronRight = 0.022474521423288 --> dCL/dAileronLeft = 0.02252467496203685 --> dCL/dElevator = 0.005432144424885712 --> dCL/dRudder = -2.654020388411257e-06 ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m3.398s user 0m2.612s sys 0m1.108s + status=0 + set +x ================================================= data/session06/2_avl_PlaneVanillaControl.py passed (as expected) ================================================= ================================================= 3_avl_TransportGeom.py test; + python 3_avl_TransportGeom.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Viewing transport bodies... MESSAGE:: Building wingOml MESSAGE:: Building wingHinges MESSAGE:: Building htailOml MESSAGE:: Building htailHinges MESSAGE:: Building vtailOml MESSAGE:: Building vtailHinges ==> Create AVL aim... ==> Viewing avl bodies... ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m45.373s user 1m9.912s sys 9m18.866s + status=0 + set +x ================================================= data/session06/3_avl_TransportGeom.py passed (as expected) ================================================= ================================================= 4_avl_TransportControl.py test; + python 4_avl_TransportControl.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Creating AVL aim... MESSAGE:: Building wingOml MESSAGE:: Building wingHinges MESSAGE:: Building htailOml MESSAGE:: Building htailHinges MESSAGE:: Building vtailOml MESSAGE:: Building vtailHinges Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice control surface data VLM control surface name - HtailControl_1 VLM control surface name - VtailControl_1 VLM control surface name - WingControl_1 VLM control surface name - WingControl_2 VLM control surface name - WingControl_3 VLM control surface name - WingControl_4 Done getting vortex lattice control surface data Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control htailControl1 not found in controls tuple! Only defaults will be used. Warning: Control VtailControl1 not found in controls tuple! Only defaults will be used. Warning: Control VtailControl1 not found in controls tuple! Only defaults will be used. Warning: Control WingControl1 not found in controls tuple! Only defaults will be used. Warning: Control WingControl1 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl3 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl2 not found in controls tuple! Only defaults will be used. Warning: Control WingControl4 not found in controls tuple! Only defaults will be used. Warning: Control WingControl4 not found in controls tuple! Only defaults will be used. Writing surface - Htail (ID = 0) Section 1 of 7 (ID = 0) Section 2 of 7 (ID = 3) Control surface 1 of 1 Section 3 of 7 (ID = 4) Control surface 1 of 1 Section 4 of 7 (ID = 1) Section 5 of 7 (ID = 5) Control surface 1 of 1 Section 6 of 7 (ID = 6) Control surface 1 of 1 Section 7 of 7 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 4 (ID = 1) Section 2 of 4 (ID = 3) Control surface 1 of 1 Section 3 of 4 (ID = 2) Control surface 1 of 1 Section 4 of 4 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 17 (ID = 0) Section 2 of 17 (ID = 5) Control surface 1 of 1 Section 3 of 17 (ID = 6) Control surface 1 of 1 Section 4 of 17 (ID = 7) Control surface 1 of 1 Section 5 of 17 (ID = 8) Control surface 1 of 1 Section 6 of 17 (ID = 4) Section 7 of 17 (ID = 9) Control surface 1 of 1 Section 8 of 17 (ID = 10) Control surface 1 of 1 Section 9 of 17 (ID = 1) Section 10 of 17 (ID = 11) Control surface 1 of 1 Section 11 of 17 (ID = 12) Control surface 1 of 1 Section 12 of 17 (ID = 3) Section 13 of 17 (ID = 13) Control surface 1 of 1 Section 14 of 17 (ID = 14) Control surface 1 of 1 Section 15 of 17 (ID = 15) Control surface 1 of 1 Section 16 of 17 (ID = 16) Control surface 1 of 1 Section 17 of 17 (ID = 2) ==> Some stability derivatives --> CLa = 5.329631106527806 --> CLb = 2.340459949869399e-09 --> CLp' = -6.892813013297252e-10 --> CLq' = 28.72846789655086 --> CLr' = -2.309119827452164e-09 --> Xcg = 55.4263 --> Xnp = 91.29113418321558 --> StaticMargin = 1.6523694378606526 --> htailControl1 {'CLtot': 0.008154370248292, 'CYtot': 2.813986432584e-12, "Cl'tot": 2.08699843511e-13, 'Cmtot': -0.03748884211962, "Cn'tot": -7.732451763366e-13, 'CDff': 0.001133243694143, 'e': -0.003225847720109} --> VtailControl1 {'CLtot': -3.241922744348e-11, 'CYtot': 0.001746902737729, "Cl'tot": 0.0001578887959999, 'Cmtot': 1.571459508788e-10, "Cn'tot": -0.0009155267108515, 'CDff': 3.677034604137e-12, 'e': -4.52516272513e-11} --> WingControl1 {'CLtot': 0.002454272405595, 'CYtot': 0.0001047561417656, "Cl'tot": 0.0008699288714424, 'Cmtot': -0.006084028396847, "Cn'tot": 0.0001105827011036, 'CDff': 4.762255976919e-05, 'e': 0.002671723867878} --> WingControl2 {'CLtot': 0.008875217380741, 'CYtot': 1.602979513829e-13, "Cl'tot": -6.234890131613e-14, 'Cmtot': -0.01681584087554, "Cn'tot": -9.439960497524e-14, 'CDff': 0.0003695415158205, 'e': 0.00723113066902} --> WingControl3 {'CLtot': 0.005956182105971, 'CYtot': -1.115588866144e-13, "Cl'tot": 3.487225159544e-14, 'Cmtot': -0.005500424236486, "Cn'tot": 4.663182804688e-14, 'CDff': 0.0007054644644664, 'e': -0.000787426314077} --> WingControl4 {'CLtot': 0.002454272404883, 'CYtot': -0.0001047561417223, "Cl'tot": -0.000869928871482, 'Cmtot': -0.0060840283936, "Cn'tot": -0.0001105827011417, 'CDff': 4.762255973538e-05, 'e': 0.002671723868034} ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m46.857s user 1m10.369s sys 9m13.618s + status=0 + set +x ================================================= data/session06/4_avl_TransportControl.py passed (as expected) ================================================= ================================================= 5_avl_TransportEigen.py test; + python 5_avl_TransportEigen.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Create AVL aim... ==> Running Analysis MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Writing mass properties file: caps.mass Parsing MassProp ==> Outputs --> Xcg = 89.3122 meter --> Xnp = 92.4391277110255 meter --> StaticMargin = 0.47265167902946065 --> EigenValues {'case 1': [[-3.1240286, 0.0], [0.019757061, 0.97330897], [0.019757061, -0.97330897], [-0.01302709, 0.0], [-0.32616585, 0.92439209], [-0.32616585, -0.92439209], [-0.013243777, 0.13183874], [-0.013243777, -0.13183874]]} --> Real Eigen Values = [-3.1240286, 0.019757061, 0.019757061, -0.01302709, -0.32616585, -0.32616585, -0.013243777, -0.013243777] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m13.447s user 0m16.416s sys 2m7.130s + status=0 + set +x ================================================= data/session06/5_avl_TransportEigen.py passed (as expected) ================================================= ================================================= 6_avl_masstran_Geom.py test; + python 6_avl_masstran_Geom.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Vewing AVL geometry MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml ==> Vewing Masstran geometry ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m12.146s user 0m15.585s sys 2m10.577s + status=0 + set +x ================================================= data/session06/6_avl_masstran_Geom.py passed (as expected) ================================================= ================================================= 7_avl_masstran_Eigen.py test; + python 7_avl_masstran_Eigen.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Creating masstran aim... ==> Creating AVL aim... ==> Running Analysis MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wingSkin, index = 1 Name = fuseSkin, index = 2 Name = htailSkin, index = 3 Name = vtailSkin, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 5460 Number of elements = 10916 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 10916 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 4599 Number of elements = 9194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 9194 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2722 Number of elements = 5440 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 5440 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 18403 Combined Number of elements = 36790 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 36790 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuseSkin Property name - htailSkin Property name - vtailSkin Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Writing mass properties file: caps.mass Parsing MassProp ==> Outputs --> Xcg = 89.6946 meter --> Xnp = 92.42426710690202 meter --> StaticMargin = 0.4126036354213024 --> EigenValues {'case 1': [[-0.70465113, 0.0], [0.13846755, 0.5514659], [0.13846755, -0.5514659], [-0.16142759, 0.51358138], [-0.16142759, -0.51358138], [-0.0068180509, 0.0], [-0.016473652, 0.12085978], [-0.016473652, -0.12085978]]} --> Real Eigen Values = [-0.70465113, 0.13846755, 0.13846755, -0.16142759, -0.16142759, -0.0068180509, -0.016473652, -0.016473652] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m16.982s user 0m21.450s sys 1m42.057s + status=0 + set +x ================================================= data/session06/7_avl_masstran_Eigen.py passed (as expected) ================================================= ================================================= 8_avl_friction_Link.py test; + python 8_avl_friction_Link.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../ESP/transport.csm"... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Lifting Surface: Body = 1, units ft XLE: 118.390617 -97.671924 3.992604 XTE: 123.551941 -97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 2, units ft XLE: 50.000000 0.000000 -8.000000 XTE: 97.200785 -0.000000 -7.176107 Chord: 47.207975 Arc: 97.395848 T/C: 0.145499 Type: Wing Lifting Surface: Body = 3, units ft XLE: 118.390617 97.671924 3.992604 XTE: 123.551941 97.671924 4.717949 Chord: 5.212043 Arc: 10.531921 T/C: 0.153243 Type: Wing Lifting Surface: Body = 4, units ft XLE: 75.304787 36.138982 -3.562691 XTE: 97.933561 36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 5, units ft XLE: 75.304787 -36.138982 -3.562691 XTE: 97.933561 -36.138982 -2.376767 Chord: 22.659828 Arc: 46.801094 T/C: 0.167991 Type: Wing Lifting Surface: Body = 6, units ft XLE: 165.023151 -35.780198 13.605316 XTE: 173.282263 -35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 7, units ft XLE: 135.000000 0.000000 6.000000 XTE: 160.026192 -0.000000 6.000000 Chord: 25.026192 Arc: 50.556450 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 8, units ft XLE: 165.023151 35.780198 13.605316 XTE: 173.282263 35.780198 13.605316 Chord: 8.259112 Arc: 16.684575 T/C: 0.080010 Type: Horizontal_Tail Lifting Surface: Body = 9, units ft XLE: 136.456162 0.000000 9.001500 XTE: 159.447890 -0.000000 9.001500 Chord: 22.991728 Arc: 46.446544 T/C: 0.080010 Type: Vertical_Tail Lifting Surface: Body = 10, units ft XLE: 162.940713 0.000000 35.486051 XTE: 169.379597 -0.000000 35.486051 Chord: 6.438884 Arc: 13.007456 T/C: 0.080010 Type: Vertical_Tail Number of sections 7, number of revolution sections 0 Number of Mach-Altitude cases = 1 Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) --> Mach = [0.1, 0.2, 0.30000000000000004, 0.4, 0.5, 0.6, 0.7000000000000001] --> CDp = [0.01592, 0.01416, 0.01323, 0.01259, 0.01209, 0.01167, 0.0113] --> CD = [0.024550602209885, 0.02466896350126383, 0.02487666257532431, 0.02519203549493851, 0.02564765931511626, 0.02630248998863598, 0.02727263653465213] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m23.909s user 0m23.899s sys 2m10.438s + status=0 + set +x ================================================= data/session06/8_avl_friction_Link.py passed (as expected) ================================================= ================================================= avl_masstran_MainGear.py test; + python avl_masstran_MainGear.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Create masstran aim... ==> Computing mass properties... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wingSkin, index = 1 Name = fuseSkin, index = 2 Name = htailSkin, index = 3 Name = vtailSkin, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 5460 Number of elements = 10916 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 10916 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 4599 Number of elements = 9194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 9194 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2722 Number of elements = 5440 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 5440 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 18403 Combined Number of elements = 36790 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 36790 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - Unobtainium No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuseSkin Property name - htailSkin Property name - vtailSkin Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input ==> Computed mass properties... --> aircraft_skin = {'mass': <Quantity 37678.41936443 kg>, 'CG': <Quantity [28.71060165257, 0.0004847831046229, 0.3509074373674] meter>, 'massInertia': <Quantity [3048890.7105, 5626736.457971, 8319844.174801, 317.8387049219, 521075.1785922, 50.57897871597] m2.kg>} ==> Creating AVL aim... ==> Outputs Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Writing mass properties file: caps.mass Parsing MassProp --> Xcg = 89.1649 meter --> Xnp = 92.42451155527696 meter --> StaticMargin = 0.4927075445822236 --> EigenValues {'case 1': [[-0.70485396, 0.0], [0.13848719, 0.55142164], [0.13848719, -0.55142164], [-0.16432037, 0.56448129], [-0.16432037, -0.56448129], [-0.0068132785, 0.0], [-0.013683559, 0.11022263], [-0.013683559, -0.11022263]]} --> Real Eigen Values = [-0.70485396, 0.13848719, 0.13848719, -0.16432037, -0.16432037, -0.0068132785, -0.013683559, -0.013683559] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m17.154s user 0m21.549s sys 1m51.701s + status=0 + set +x ================================================= solutions/session06/avl_masstran_MainGear.py passed (as expected) ================================================= ================================================= avl_masstran_MultiMat.py test; + python avl_masstran_MultiMat.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Create masstran aim... ==> Computing mass properties... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wingSkin, index = 1 Name = fuseSkin, index = 2 Name = htailSkin, index = 3 Name = vtailSkin, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 5460 Number of elements = 10916 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 10916 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 4599 Number of elements = 9194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 9194 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2722 Number of elements = 5440 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 5440 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 18403 Combined Number of elements = 36790 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 36790 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 3 Material name - fuseium No "materialType" specified for Material tuple fuseium, defaulting to "Isotropic" Material name - tailium No "materialType" specified for Material tuple tailium, defaulting to "Isotropic" Material name - wingium No "materialType" specified for Material tuple wingium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuseSkin Property name - htailSkin Property name - vtailSkin Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input ==> Computed mass properties... --> aircraft_skin = {'mass': <Quantity 52814.21122638 kg>, 'CG': <Quantity [25.21427105317, 9.440962788246e-05, 0.007142713640016] meter>, 'massInertia': <Quantity [3041321.23867, 6969066.307863, 9624742.735327, 86.32824029324, 262896.8536944, 25.61592047072] m2.kg>} ==> Creating AVL aim... ==> Outputs Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 3 Name = Wing, index = 1 Name = Htail, index = 2 Name = Vtail, index = 3 Getting vortex lattice surface data VLM surface name - Htail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Vtail No "groupName" variable provided or no matches found, going to use tuple name VLM surface name - Wing No "groupName" variable provided or no matches found, going to use tuple name Done getting vortex lattice surface data Writing surface - Htail (ID = 0) Section 1 of 3 (ID = 0) Section 2 of 3 (ID = 1) Section 3 of 3 (ID = 2) Writing surface - Vtail (ID = 1) Section 1 of 2 (ID = 1) Section 2 of 2 (ID = 0) Writing surface - Wing (ID = 2) Section 1 of 5 (ID = 0) Section 2 of 5 (ID = 4) Section 3 of 5 (ID = 1) Section 4 of 5 (ID = 3) Section 5 of 5 (ID = 2) Writing mass properties file: caps.mass Parsing MassProp --> Xcg = 80.225 meter --> Xnp = 92.49086831365985 meter --> StaticMargin = 1.8540509372070697 --> EigenValues {'case 1': [[-0.67265797, 0.0], [0.12206579, 0.57566948], [0.12206579, -0.57566948], [-0.15648068, 1.0547055], [-0.15648068, -1.0547055], [-0.0068086674, 0.0], [-0.00032991877, 0.049308008], [-0.00032991877, -0.049308008]]} --> Real Eigen Values = [-0.67265797, 0.12206579, 0.12206579, -0.15648068, -0.15648068, -0.0068086674, -0.00032991877, -0.00032991877] ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m17.326s user 0m22.434s sys 2m19.502s + status=0 + set +x ================================================= solutions/session06/avl_masstran_MultiMat.py passed (as expected) ================================================= ================================================= masstran_MultiAIM.py test; + python masstran_MultiAIM.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Loading masstran aims... ==> Computing mass properties... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = fuseSkin, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 7445 Number of elements = 14886 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 14886 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - fuseium No "materialType" specified for Material tuple fuseium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - fuseSkin Done getting FEA properties Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 1 Name = wingSkin, index = 1 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - wingium No "materialType" specified for Material tuple wingium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 1 Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 2 Name = htailSkin, index = 1 Name = vtailSkin, index = 2 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 3488 Number of elements = 6972 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 6972 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 3480 Number of elements = 6956 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 6956 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 6968 Combined Number of elements = 13928 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 13928 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 1 Material name - tailium No "materialType" specified for Material tuple tailium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 2 Property name - htailSkin Property name - vtailSkin Done getting FEA properties Updating mesh element types based on properties input ==> Computed mass properties... --> fuse_skin = {'mass': <Quantity 7849.475274166 kg>, 'CG': <Quantity [23.60861887848, -5.594392309561e-05, 0.1631067332576] meter>, 'massInertia': <Quantity [64256.8299145, 1266909.722239, 1265121.586758, -7.997972200033, 26539.85606389, -0.8824247963621] m2.kg>} --> wing_skin = {'mass': <Quantity 23992.67003648 kg>, 'CG': <Quantity [26.65600801849, 3.498760694631e-05, -0.6718794767923] meter>, 'massInertia': <Quantity [4029452.651317, 529853.8379245, 4523798.230161, -19.40420203835, 69301.12468094, 23.37530324142] m2.kg>} --> tail_skin = {'mass': <Quantity 748.6464447904 kg>, 'CG': <Quantity [47.57149390357, -1.456429516565e-06, 3.576129105462] meter>, 'massInertia': <Quantity [19383.57137666, 6924.661310072, 21171.65394983, 0.005003805341831, 1134.160383177, 0.004686577588248] m2.kg>} ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m7.686s user 0m8.594s sys 0m1.577s + status=0 + set +x ================================================= solutions/session06/masstran_MultiAIM.py passed (as expected) ================================================= ================================================= masstran_MultiMat.py test; + python masstran_MultiMat.py + tee -a /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/training.log ==> Loading geometry from file "../../data/ESP/transport.csm"... ==> Setting Build Variables and Geometry Values... ==> Loading masstran aim... ==> Computing mass properties... MESSAGE:: Building wingOml MESSAGE:: Building htailOml MESSAGE:: Building vtailOml MESSAGE:: Building fuseOml Mapping Csys attributes ................ Number of unique Csys attributes = 0 Getting FEA coordinate systems....... Number of coordinate systems - 0 No coordinate systems found - defaulting to global Mapping capsConstraint attributes ................ Number of unique capsConstraint attributes = 0 Mapping capsLoad attributes ................ Number of unique capsLoad attributes = 0 Mapping capsBound attributes ................ Number of unique capsBound attributes = 0 Mapping capsConnect attributes ................ Number of unique capsConnect attributes = 0 Mapping capsGroup attributes ................ Number of unique capsGroup attributes = 4 Name = wingSkin, index = 1 Name = fuseSkin, index = 2 Name = htailSkin, index = 3 Name = vtailSkin, index = 4 Setting FEA Data Mesh for body = 0 Number of nodal coordinates = 5622 Number of elements = 11240 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 11240 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 1 Number of nodal coordinates = 5460 Number of elements = 10916 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 10916 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 2 Number of nodal coordinates = 4599 Number of elements = 9194 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 9194 Elemental Quad4 = 0 Setting FEA Data Mesh for body = 3 Number of nodal coordinates = 2722 Number of elements = 5440 Elemental Nodes = 0 Elemental Rods = 0 Elemental Tria3 = 5440 Elemental Quad4 = 0 Combining multiple FEA meshes! Combined Number of nodal coordinates = 18403 Combined Number of elements = 36790 Combined Elemental Nodes = 0 Combined Elemental Rods = 0 Combined Elemental Tria3 = 36790 Combined Elemental Quad4 = 0 Getting FEA materials....... Number of materials - 3 Material name - fuseium No "materialType" specified for Material tuple fuseium, defaulting to "Isotropic" Material name - tailium No "materialType" specified for Material tuple tailium, defaulting to "Isotropic" Material name - wingium No "materialType" specified for Material tuple wingium, defaulting to "Isotropic" Done getting FEA materials Getting FEA properties....... Number of properties - 4 Property name - fuseSkin Property name - htailSkin Property name - vtailSkin Property name - wingSkin Done getting FEA properties Updating mesh element types based on properties input ==> Computed mass properties... --> aircraft_skin = {'mass': <Quantity 71849.22261512026 lb>, 'CG': <Quantity [86.62567835984251, 0.0003073154573033464, -1.2243299067857611] ft>, 'massInertia': <Quantity [97984636.59227683, 52633549.11469667, 147324437.64378545, 650.3192749128308, 3464172.518822185, 692.2833235637139] lb*ft^2>} ----------------------------------------------------- Suppressions used: count bytes template 2 96 *PyFloat_FromDouble* 3 240 *numpy* ----------------------------------------------------- real 0m6.909s user 0m7.812s sys 0m1.315s + status=0 + set +x ================================================= solutions/session06/masstran_MultiMat.py passed (as expected) ================================================= mv: cannot stat '/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/training/2023/data/ESP/viewVLM.udc.bak': No such file or directory 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