--> Cl = [2.01724970524547e-16, 0.1, 0.150000000000233, 0.300000000000164, 0.4]
--> Cd = [0.00617285381077275, 0.00623021348482652, 0.00630554753826838, 0.00680929883615129, 0.00747424244864973]
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 0m3.047s
user 0m2.683s
sys 0m0.714s
+ status=0
+ set +x
=================================================
data/session03/04_xfoil_MultiAnalysis.py passed (as expected)
=================================================
=================================================
05_xfoil_Camber_Plot.py test;
+ python 05_xfoil_Camber_Plot.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "naca.csm"...
==> Creating xfoilAIM
==> Setting analysis values
==> Retrieve analysis results. camber = 0.0
==> Retrieve analysis results. camber = 0.01
==> Retrieve analysis results. camber = 0.04
==> Retrieve analysis results. camber = 0.07
==> Plotting analysis results (close plot window to finish Python script
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 0m11.708s
user 0m10.955s
sys 0m1.079s
+ status=0
+ set +x
=================================================
data/session03/05_xfoil_Camber_Plot.py passed (as expected)
=================================================
=================================================
05_xfoil_Camber.py test;
+ python 05_xfoil_Camber.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "naca.csm"...
==> Creating xfoilAIM
==> Setting analysis values
==> Retrieve analysis results. camber = 0.0
==> Retrieve analysis results. camber = 0.01
==> Retrieve analysis results. camber = 0.04
==> Retrieve analysis results. camber = 0.07
--> Cambers = [0.0, 0.01, 0.04, 0.07]
--> Alpha = [[0.0, 1.0, 3.0], [0.0, 1.0, 3.0], [0.0, 1.0, 3.0], [0.0, 1.0]]
--> Cl = [[-3.53757498051076e-07, 0.126697477361204, 0.377437462181212], [0.140339949737252, 0.266469023977195, 0.514670926888577], [0.554542727545664, 0.680708956698693, 0.940291957324787], [0.919771481559933, 1.03861131519266]]
--> Cd = [[0.00617285380994943, 0.00627268560115553, 0.00729426778763046], [0.00625861871528289, 0.00622635244564165, 0.00706717658622418], [0.00787687247022659, 0.00739456756393865, 0.0078213365172423], [0.00972065010478373, 0.0101041953398562]]
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 0m6.309s
user 0m5.620s
sys 0m0.999s
+ status=0
+ set +x
=================================================
data/session03/05_xfoil_Camber.py passed (as expected)
=================================================
=================================================
06_xfoil_CleanDirty.py test;
+ python 06_xfoil_CleanDirty.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "naca.csm"...
==> Creating xfoilAIM
1. No Errors --------------------------------------------------------------------------------
==> Setting alpha sequence
==> Running preAnalysis
==> Running xFoil......
==> Running postAnalysis
--> Cl = [-3.53757498051076e-07, 0.377437462009088, 0.642259371967933, 0.955175654912633, 1.00909750957732]
2. DIRTY AnalysisVal Error --------------------------------------------------------------------------------
==> Setting new alpha sequence
==> Attempting to get Cl
==> CAPSError = CAPS_DIRTY:
================================================================================
================================================================================
==> Running preAnalysis
==> Running xFoil......
==> Running postAnalysis
==> Attempting to get Cl
--> Cl = 0.252764696628452
3. DIRTY GeometryVal Error --------------------------------------------------------------------------------
==> Modifying camber
==> Attempting to get Cl
==> CAPSError = CAPS_DIRTY:
================================================================================
================================================================================
==> Running preAnalysis
==> Running xFoil......
==> Running postAnalysis
==> Attempting to get Cl
--> Cl = [1.03861130997367, 1.15325582947821]
4. DIRTY pre- but no postAnalysis Error --------------------------------------------------------------------------------
==> Modifying Mach
==> Running preAnalysis but not running postAnalysis
==> Attempting to get Cl
==> CAPSError = CAPS_DIRTY:
================================================================================
================================================================================
==> Running xFoil......
==> Running postAnalysis
==> Attempting to get Cl
--> Cl = [0.967203918356169, 1.07899610948988]
5. CLEAN Error --------------------------------------------------------------------------------
==> Running preAnalysis
==> CAPSError = CAPS_CLEAN:
================================================================================
================================================================================
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 0m5.071s
user 0m4.429s
sys 0m0.985s
+ status=0
+ set +x
=================================================
data/session03/06_xfoil_CleanDirty.py passed (as expected)
=================================================
=================================================
07_masstran_f118_AIM.py test;
+ python 07_masstran_f118_AIM.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "f118-B.csm"...
==> Geometry used by masstranAll instance with no capsIntent
==> Geometry used by Wing instance with capsIntent='wing'
==> Geometry used by Tail instance with capsIntent='tail'
==> Geometry used by WingFuse instance with capsIntent=['wing','fuse']
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 0m1.901s
user 0m1.515s
sys 0m0.722s
+ status=0
+ set +x
=================================================
data/session03/07_masstran_f118_AIM.py passed (as expected)
=================================================
=================================================
08_masstran_f118_Wing.py test;
+ python 08_masstran_f118_Wing.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/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 = 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 0m1.586s
user 0m1.296s
sys 0m0.635s
+ 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/7.8/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 0m1.982s
user 0m1.683s
sys 0m0.663s
+ 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/7.8/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 0m1.746s
user 0m1.444s
sys 0m0.665s
+ 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/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
f118-C.csm test;
+ /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/ESP/LINUX64/bin/serveESP -batch -verify -outLevel 0 f118-C.csm
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
WARNING:: cannot open "./verify_7.8.0/f118-C.vfy", so verification is being skipped
==> serveESP completed successfully with no verification data
real 0m0.171s
user 0m0.124s
sys 0m0.113s
+ 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/7.8/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 0m3.822s
user 0m3.262s
sys 0m0.899s
+ 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/7.8/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 0m1.449s
user 0m1.230s
sys 0m0.566s
+ 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/7.8/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 0m1.440s
user 0m1.246s
sys 0m0.579s
+ 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/7.8/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 0m2.711s
user 0m2.184s
sys 0m1.150s
+ status=0
+ set +x
=================================================
solutions/session03/masstran_CG.py passed (as expected)
=================================================
=================================================
+ echo 'f118-D.csm test;'
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
f118-D.csm test;
+ /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/ESP/LINUX64/bin/serveESP -batch -verify -outLevel 0 f118-D.csm
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
WARNING:: cannot open "./verify_7.8.0/f118-D.vfy", so verification is being skipped
==> serveESP completed successfully with no verification data
real 0m0.183s
user 0m0.174s
sys 0m0.075s
+ status=0
+ set +x
=================================================
data/session04/f118-D passed (as expected)
=================================================
=================================================
+ echo 'naca.csm test;'
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
naca.csm test;
+ /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/ESP/LINUX64/bin/serveESP -batch -verify -outLevel 0 naca.csm
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
WARNING:: cannot open "./verify_7.8.0/naca.vfy", so verification is being skipped
==> serveESP completed successfully with no verification data
real 0m0.174s
user 0m0.144s
sys 0m0.049s
+ 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/7.8/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 0m5.201s
user 0m4.950s
sys 0m0.604s
+ status=0
+ set +x
=================================================
data/session04/1_mses_Deriv.py passed (as expected)
=================================================
=================================================
2_mses_DerivPlot_CD_Alpha.py test;
+ python 2_mses_DerivPlot_CD_Alpha.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "naca.csm"...
--> Alpha -3.0
--> Alpha -2.5714285714285716
--> Alpha -2.142857142857143
--> Alpha -1.7142857142857144
--> Alpha -1.2857142857142858
--> Alpha -0.8571428571428572
--> Alpha -0.4285714285714288
--> Alpha 0.0
--> Alpha 0.4285714285714284
--> Alpha 0.8571428571428568
--> Alpha 1.2857142857142856
--> Alpha 1.7142857142857144
--> Alpha 2.1428571428571423
--> Alpha 2.571428571428571
--> Alpha 3.0
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 1m1.425s
user 0m59.529s
sys 0m2.736s
+ status=0
+ set +x
=================================================
data/session04/2_mses_DerivPlot_CD_Alpha.py passed (as expected)
=================================================
=================================================
3_mses_OpenMDAO_CD_Alpha.py test;
+ python 3_mses_OpenMDAO_CD_Alpha.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/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 0m29.648s
user 0m28.863s
sys 0m1.696s
+ status=0
+ set +x
=================================================
data/session04/3_mses_OpenMDAO_CD_Alpha.py passed (as expected)
=================================================
=================================================
4_mses_DerivPlot_CD_camber.py test;
+ python 4_mses_DerivPlot_CD_camber.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "naca.csm"...
--> camber -0.1
Getting CFD design variables.......
Number of design variables - 1
Design Variable name - camber
Done getting CFD design variables
--> camber -0.08571428571428572
--> camber -0.07142857142857142
--> camber -0.05714285714285715
--> camber -0.04285714285714286
--> camber -0.028571428571428567
--> camber -0.01428571428571429
--> camber 0.0
--> camber 0.01428571428571429
--> camber 0.02857142857142858
--> camber 0.04285714285714287
--> camber 0.05714285714285716
--> camber 0.07142857142857142
--> camber 0.08571428571428572
--> camber 0.1
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 1m6.224s
user 1m3.850s
sys 0m3.303s
+ status=0
+ set +x
=================================================
data/session04/4_mses_DerivPlot_CD_camber.py passed (as expected)
=================================================
=================================================
5_mses_OpenMDAO_CD_camber.py test;
+ python 5_mses_OpenMDAO_CD_camber.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/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 [0.1]
--> CD_camber [[0.17593485]]
RUNNING THE L-BFGS-B CODE
* * *
Machine precision = 2.220D-16
N = 1 M = 10
At X0 1 variables are exactly at the bounds
At iterate 0 f= 1.37022D-02 |proj g|= 1.75935D-01
--> camber [-0.07593485]
--> CD [0.01053684]
--> camber [-0.07593485]
--> CD_camber [[-0.07712924]]
At iterate 1 f= 1.05368D-02 |proj g|= 7.71292D-02
--> camber [-0.02231317]
--> CD [0.00803517]
--> camber [-0.02231317]
--> CD_camber [[-0.0171107]]
At iterate 2 f= 8.03517D-03 |proj g|= 1.71107D-02
--> camber [-0.00702616]
--> CD [0.0078537]
--> camber [-0.00702616]
--> CD_camber [[-0.00523684]]
At iterate 3 f= 7.85370D-03 |proj g|= 5.23684D-03
--> camber [-0.00028399]
--> CD [0.00783468]
--> camber [-0.00028399]
--> CD_camber [[-0.00015055]]
At iterate 4 f= 7.83468D-03 |proj g|= 1.50554D-04
--> camber [-8.4421087e-05]
--> CD [0.00783469]
--> camber [-8.4421087e-05]
--> CD_camber [[-6.01565391e-07]]
--> camber [-0.00023734]
--> CD [0.00783468]
--> camber [-0.00023734]
--> CD_camber [[-0.00011549]]
At iterate 5 f= 7.83468D-03 |proj g|= 1.15490D-04
* * *
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 7 5 0 0 1.155D-04 7.835D-03
F = 7.8346804870798696E-003
CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH
Optimization Complete
-----------------------------------
--> Optimized value: [-0.00023734]
sys:1: ResourceWarning: unclosed file <_io.TextIOWrapper name='drag_COBYLA.dat' mode='w' encoding='UTF-8'>
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
102 9208 *scipy*
-----------------------------------------------------
real 0m35.766s
user 0m34.521s
sys 0m2.186s
+ status=0
+ set +x
=================================================
data/session04/5_mses_OpenMDAO_CD_camber.py passed (as expected)
=================================================
=================================================
6_mses_DerivPlot_CL2_camber.py test;
+ python 6_mses_DerivPlot_CL2_camber.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Loading geometry from file "naca.csm"...
--> camber -0.1
Getting CFD design variables.......
Number of design variables - 1
Design Variable name - camber
Done getting CFD design variables
--> camber -0.08571428571428572
--> camber -0.07142857142857142
--> camber -0.05714285714285715
--> camber -0.04285714285714286
--> camber -0.028571428571428567
--> camber -0.01428571428571429
--> camber 0.0
--> camber 0.01428571428571429
--> camber 0.02857142857142858
--> camber 0.04285714285714287
--> camber 0.05714285714285716
--> camber 0.07142857142857142
--> camber 0.08571428571428572
--> camber 0.1
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
-----------------------------------------------------
real 1m6.512s
user 1m4.198s
sys 0m3.240s
+ status=0
+ set +x
=================================================
data/session04/6_mses_DerivPlot_CL2_camber.py passed (as expected)
=================================================
=================================================
7_mses_OpenMDAO_CL2_camber.py test;
+ python 7_mses_OpenMDAO_CL2_camber.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/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
--> CL2 [1.23492174]
--> camber [0.1]
--> CL2 [1.23492174]
--> camber [0.1]
--> CL2_camber [[14.37217996]]
RUNNING THE L-BFGS-B CODE
* * *
Machine precision = 2.220D-16
N = 1 M = 10
At X0 1 variables are exactly at the bounds
At iterate 0 f= 1.23492D+00 |proj g|= 2.00000D-01
--> camber [-0.1]
--> CL2 [1.23490353]
--> camber [-0.1]
--> CL2_camber [[-14.37225247]]
--> camber [9.9145125e-05]
--> CL2 [1.68365045e-06]
--> camber [9.9145125e-05]
--> CL2_camber [[0.03419083]]
At iterate 1 f= 1.68365D-06 |proj g|= 3.41908D-02
--> camber [-0.00013908]
--> CL2 [3.35065161e-06]
--> camber [-0.00013908]
--> CL2_camber [[-0.04823346]]
--> camber [2.4649602e-07]
--> CL2 [1.23332697e-12]
--> camber [2.4649602e-07]
--> CL2_camber [[-2.92631678e-05]]
At iterate 2 f= 1.23333D-12 |proj g|= 2.92632D-05
--> camber [3.31068759e-07]
--> CL2 [8.77129217e-14]
--> camber [3.31068759e-07]
--> CL2_camber [[7.80397748e-06]]
At iterate 3 f= 8.77129D-14 |proj g|= 7.80398D-06
* * *
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 3 6 3 0 0 7.804D-06 8.771D-14
F = 8.7712921654217113E-014
CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH
Optimization Complete
-----------------------------------
--> Optimized value: [3.31068759e-07]
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
102 9208 *scipy*
-----------------------------------------------------
real 0m32.553s
user 0m31.369s
sys 0m2.119s
+ status=0
+ set +x
=================================================
data/session04/7_mses_OpenMDAO_CL2_camber.py passed (as expected)
=================================================
=================================================
8_mses_OpenMDAO_CDCL.py test;
+ python 8_mses_OpenMDAO_CDCL.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Starting Optimization...
--> Alpha [0.]
--> camber [0.1]
Getting CFD design variables.......
Number of design variables - 1
Design Variable name - camber
Done getting CFD design variables
--> CD [0.01370215]
--> CL [1.11127033]
--> Alpha [0.]
--> camber [0.1]
--> CD [0.01370215]
--> CL [1.11127033]
--> Alpha [0.]
--> camber [0.1]
--> CD_Alpha [[0.00105841]]
--> CL_Alpha [[0.09897622]]
--> CD_camber [[0.17593485]]
--> CL_camber [[6.46655435]]
--> Alpha [0.00077914]
--> camber [0.04412056]
--> CD [0.00864294]
--> CL [0.57036568]
--> Alpha [0.00077914]
--> camber [0.04412056]
--> CD_Alpha [[0.00023873]]
--> CL_Alpha [[0.12984106]]
--> CD_camber [[0.03642485]]
--> CL_camber [[12.53399098]]
--> Alpha [0.00103084]
--> camber [0.05844972]
--> CD [0.00930221]
--> CL [0.74439496]
--> Alpha [0.00103084]
--> camber [0.05844972]
--> CD_Alpha [[0.00033987]]
--> CL_Alpha [[0.12673074]]
--> CD_camber [[0.05177196]]
--> CL_camber [[11.83402744]]
--> Alpha [0.00125705]
--> camber [0.05892094]
--> CD [0.00932812]
--> CL [0.74994607]
Optimization terminated successfully (Exit mode 0)
Current function value: 0.009328121196209568
Iterations: 3
Function evaluations: 4
Gradient evaluations: 3
Optimization Complete
-----------------------------------
--> Optimized value: [0.05892094]
-----------------------------------------------------
Suppressions used:
count bytes template
2 96 *PyFloat_FromDouble*
3 240 *numpy*
102 9208 *scipy*
-----------------------------------------------------
real 0m28.482s
user 0m27.711s
sys 0m1.934s
+ status=0
+ set +x
=================================================
data/session04/8_mses_OpenMDAO_CDCL.py passed (as expected)
=================================================
=================================================
9_masstran_OpenMDAO_thick.py test;
+ python 9_masstran_OpenMDAO_thick.py
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
==> Starting Optimization...
/jenkins/workspace/ESP_MemcheckCaps/7.8/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/7.8/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/7.8/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 0m9.537s
user 0m8.696s
sys 0m2.003s
+ status=0
+ set +x
=================================================
data/session04/9_masstran_OpenMDAO_thick.py passed (as expected)
=================================================
=================================================
masstran_OpenMDAO_geom.py test;
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
+ python masstran_OpenMDAO_geom.py
==> 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 0m9.213s
user 0m8.634s
sys 0m1.858s
+ status=0
+ set +x
=================================================
solutions/session04/masstran_OpenMDAO_geom.py passed (as expected)
=================================================
=================================================
+ echo 'avlPlaneVanilla.csm test;'
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
avlPlaneVanilla.csm test;
+ /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/ESP/LINUX64/bin/serveESP -batch -verify -outLevel 0 avlPlaneVanilla.csm
+ tee -a /jenkins/workspace/ESP_MemcheckCaps/7.8/CAPS/training/LINUX64/CAPS/training/2023/training.log
WARNING:: cannot open "./verify_7.8.0/avlPlaneVanilla.vfy", so verification is being skipped
==> serveESP completed successfully with no verification data
real 0m0.733s
user 0m0.637s
sys 0m0.159s
+ 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/7.8/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 0m3.453s
user 0m2.700s
sys 0m1.088s
+ 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/7.8/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 0m3.335s
user 0m2.558s
sys 0m1.099s
+ 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/7.8/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 0m46.036s
user 1m10.492s
sys 9m20.702s
+ 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/7.8/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 0m48.233s
user 1m7.794s
sys 10m43.091s
+ 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/7.8/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 0m13.074s
user 0m15.993s
sys 2m14.515s
+ 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/7.8/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 0m12.777s
user 0m15.815s
sys 2m1.698s
+ 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/7.8/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 0m17.280s
user 0m21.674s
sys 1m43.412s
+ 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/7.8/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 0m23.625s
user 0m23.457s
sys 2m22.045s
+ 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/7.8/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 0m17.351s
user 0m22.005s
sys 2m16.823s
+ 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/7.8/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 0m17.122s
user 0m22.022s
sys 2m16.818s
+ 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/7.8/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 0m7.745s
user 0m8.471s
sys 0m1.665s
+ 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/7.8/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 0m7.030s
user 0m7.952s
sys 0m1.281s
+ status=0
+ set +x
=================================================
solutions/session06/masstran_MultiMat.py passed (as expected)
=================================================
mv: cannot stat '/jenkins/workspace/ESP_MemcheckCaps/7.8/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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