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 = 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 /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsAnalysis.c:4201
#5 0x7fe2acb359b0 in caps_execX /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsAnalysis.c:5088
#6 0x7fe2acba2b9f in caps_updateAnalysisOut /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsValue.c:274
#7 0x7fe2acba45cd in caps_getValuX /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsValue.c:409
#8 0x7fe2acba5687 in caps_getValue /jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/CAPS/src/capsValue.c:533
#9 0x7fe2b3e08e2d (/lib/x86_64-linux-gnu/libffi.so.8+0x7e2d)
#10 0x7fe2b3e05492 (/lib/x86_64-linux-gnu/libffi.so.8+0x4492)
#11 0x7fe2b3c3e7eb in _call_function_pointer /home/jenkins/util/python/Python-3.11.9_address/Modules/_ctypes/callproc.c:923
#12 0x7fe2b3c40489 in _ctypes_callproc /home/jenkins/util/python/Python-3.11.9_address/Modules/_ctypes/callproc.c:1262
#13 0x7fe2b3c2b9be in PyCFuncPtr_call /home/jenkins/util/python/Python-3.11.9_address/Modules/_ctypes/_ctypes.c:4201
#14 0x7fe2b72e9d75 in _PyObject_MakeTpCall Objects/call.c:214
#15 0x7fe2b72ea409 in _PyObject_VectorcallTstate Include/internal/pycore_call.h:90
#16 0x7fe2b72ea499 in PyObject_Vectorcall Objects/call.c:299
#17 0x7fe2b759f454 in _PyEval_EvalFrameDefault Python/ceval.c:4769
#18 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73
#19 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434
#20 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393
#21 0x7fe2b72e8c6c in _PyVectorcall_Call Objects/call.c:245
#22 0x7fe2b72e973c in _PyObject_Call Objects/call.c:328
#23 0x7fe2b72e9861 in PyObject_Call Objects/call.c:355
#24 0x7fe2b7574663 in do_call_core Python/ceval.c:7349
#25 0x7fe2b75a76eb in _PyEval_EvalFrameDefault Python/ceval.c:5376
#26 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73
#27 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434
#28 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393
#29 0x7fe2b72eb79d in _PyObject_VectorcallTstate Include/internal/pycore_call.h:92
#30 0x7fe2b72eb79d in PyObject_CallOneArg Objects/call.c:376
#31 0x7fe2b730deb2 in property_descr_get Objects/descrobject.c:1630
#32 0x7fe2b73d30a3 in _PyObject_GenericGetAttrWithDict Objects/object.c:1278
#33 0x7fe2b73d4315 in PyObject_GenericGetAttr Objects/object.c:1368
#34 0x7fe2b73d2856 in PyObject_GetAttr Objects/object.c:916
#35 0x7fe2b758dcdc in _PyEval_EvalFrameDefault Python/ceval.c:3461
#36 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73
#37 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434
#38 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393
#39 0x7fe2b72f10e2 in _PyObject_VectorcallTstate Include/internal/pycore_call.h:92
#40 0x7fe2b72f268d in method_vectorcall Objects/classobject.c:59
#41 0x7fe2b72eb79d in _PyObject_VectorcallTstate Include/internal/pycore_call.h:92
#42 0x7fe2b72eb79d in PyObject_CallOneArg Objects/call.c:376
#43 0x7fe2b7408b54 in call_attribute Objects/typeobject.c:7665
#44 0x7fe2b742bba3 in slot_tp_getattr_hook Objects/typeobject.c:7706
#45 0x7fe2b73d2856 in PyObject_GetAttr Objects/object.c:916
#46 0x7fe2b758dcdc in _PyEval_EvalFrameDefault Python/ceval.c:3461
#47 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73
#48 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434
#49 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393
#50 0x7fe2b72e8c6c in _PyVectorcall_Call Objects/call.c:245
#51 0x7fe2b72e973c in _PyObject_Call Objects/call.c:328
#52 0x7fe2b72e9861 in PyObject_Call Objects/call.c:355
#53 0x7fe2b7574663 in do_call_core Python/ceval.c:7349
#54 0x7fe2b75a76eb in _PyEval_EvalFrameDefault Python/ceval.c:5376
#55 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73
#56 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434
#57 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393
#58 0x7fe2b72f10e2 in _PyObject_VectorcallTstate Include/internal/pycore_call.h:92
#59 0x7fe2b72f257b in method_vectorcall Objects/classobject.c:89
#60 0x7fe2b72e8c6c in _PyVectorcall_Call Objects/call.c:245
#61 0x7fe2b72e973c in _PyObject_Call Objects/call.c:328
#62 0x7fe2b72e9861 in PyObject_Call Objects/call.c:355
#63 0x7fe2b7574663 in do_call_core Python/ceval.c:7349
#64 0x7fe2b75a76eb in _PyEval_EvalFrameDefault Python/ceval.c:5376
#65 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73
#66 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434
#67 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393
#68 0x7fe2b72e8c6c in _PyVectorcall_Call Objects/call.c:245
#69 0x7fe2b72e973c in _PyObject_Call Objects/call.c:328
#70 0x7fe2b72ecaec in PyObject_CallObject Objects/call.c:450
#71 0x7fe2916c8409 in cb_calcfc_in__cobyla__user__routines (/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/ESP/venv/lib/python3.11/site-packages/scipy/optimize/_cobyla.cpython-311-x86_64-linux-gnu.so+0x3409)
#72 0x7fe2916c99b4 in cobylb_ (/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/ESP/venv/lib/python3.11/site-packages/scipy/optimize/_cobyla.cpython-311-x86_64-linux-gnu.so+0x49b4)
#73 0x7fe2916cd4b6 in cobyla_ (/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/ESP/venv/lib/python3.11/site-packages/scipy/optimize/_cobyla.cpython-311-x86_64-linux-gnu.so+0x84b6)
#74 0x7fe2916c8fc6 in f2py_rout__cobyla_minimize (/jenkins/workspace/ESP_MemcheckCaps/7.7/CAPS/training/LINUX64/ESP/venv/lib/python3.11/site-packages/scipy/optimize/_cobyla.cpython-311-x86_64-linux-gnu.so+0x3fc6)
#75 0x7fe2b72e9d75 in _PyObject_MakeTpCall Objects/call.c:214
#76 0x7fe2b72ea409 in _PyObject_VectorcallTstate Include/internal/pycore_call.h:90
#77 0x7fe2b72ea499 in PyObject_Vectorcall Objects/call.c:299
#78 0x7fe2b759f454 in _PyEval_EvalFrameDefault Python/ceval.c:4769
#79 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73
#80 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434
#81 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393
#82 0x7fe2b72e8e0e in _PyVectorcall_Call Objects/call.c:257
#83 0x7fe2b72e973c in _PyObject_Call Objects/call.c:328
#84 0x7fe2b72e9861 in PyObject_Call Objects/call.c:355
#85 0x7fe2b7574663 in do_call_core Python/ceval.c:7349
#86 0x7fe2b75a76eb in _PyEval_EvalFrameDefault Python/ceval.c:5376
#87 0x7fe2b75ac15a in _PyEval_EvalFrame Include/internal/pycore_ceval.h:73
#88 0x7fe2b75ac15a in _PyEval_Vector Python/ceval.c:6434
#89 0x7fe2b72e9a1d in _PyFunction_Vectorcall Objects/call.c:393
#90 0x7fe2b72e8e0e in _PyVectorcall_Call Objects/call.c:257
#91 0x7fe2b72e973c in _PyObject_Call Objects/call.c:328
#92 0x7fe2b72e9861 in PyObject_Call Objects/call.c:355
#93 0x7fe2b7574663 in do_call_core Python/ceval.c:7349
#94 0x7fe2b75a76eb in _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
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