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+ python tess_2_TFI_Templates.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 11092
Number of elements = 22807
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 22807
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 11092
Total number of elements = 22807
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 11921
Number of elements = 24465
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 24465
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 11921
Total number of elements = 24465

real	0m13.864s
user	0m24.375s
sys	1m7.047s
+ status=0
+ set +x

=================================================
data/session09/tess_2_TFI_Templates.py passed (as expected)
=================================================


=================================================
tess_3_Params.py test;
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log
+ python tess_3_Params.py

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 732
Number of elements = 1781
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 1781
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 732
Total number of elements = 1781
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 934
Number of elements = 2228
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 2228
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 934
Total number of elements = 2228
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 3545
Number of elements = 7669
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 7669
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3545
Total number of elements = 7669

real	0m12.347s
user	0m19.285s
sys	0m27.861s
+ status=0
+ set +x

=================================================
data/session09/tess_3_Params.py passed (as expected)
=================================================


=================================================
tess_4_Params.py test;
+ python tess_4_Params.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 1406
Number of elements = 3137
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 3137
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 1406
Total number of elements = 3137
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 2097
Number of elements = 4570
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 4570
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 2097
Total number of elements = 4570
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 6562
Number of elements = 13689
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 13689
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 6562
Total number of elements = 13689

real	0m12.238s
user	0m21.989s
sys	0m52.660s
+ status=0
+ set +x

=================================================
data/session09/tess_4_Params.py passed (as expected)
=================================================


=================================================
tess_5_Params.py test;
+ python tess_5_Params.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 3538
Number of elements = 7417
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 7417
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3538
Total number of elements = 7417
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 12458
Number of elements = 25384
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 25384
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 12458
Total number of elements = 25384
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 45075
Number of elements = 90817
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 90817
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 45075
Total number of elements = 90817

real	0m16.758s
user	0m33.768s
sys	0m59.813s
+ status=0
+ set +x

=================================================
data/session09/tess_5_Params.py passed (as expected)
=================================================


=================================================
tess_6_TriQuad.py test;
+ python tess_6_TriQuad.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 8302
Number of elements = 17191
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17191
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 8302
Total number of elements = 17191
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 72029
Number of elements = 74322
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 74322
----------------------------
Total number of nodes    = 72029
Total number of elements = 74322
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 1655
Number of elements = 3225
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 3225
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 1655
Total number of elements = 3225
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 3009
Number of elements = 2928
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 2928
----------------------------
Total number of nodes    = 3009
Total number of elements = 2928

real	0m22.934s
user	0m31.573s
sys	0m53.944s
+ status=0
+ set +x

=================================================
data/session09/tess_6_TriQuad.py passed (as expected)
=================================================


=================================================
tess_7_MeshSizing.py test;
+ python tess_7_MeshSizing.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 8302
Number of elements = 17191
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17191
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 8302
Total number of elements = 17191
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4

Getting mesh sizing parameters
	Mesh sizing name - leadingEdge
	Mesh sizing name - rootLeadingEdge
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 3919
Number of elements = 8410
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 8410
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3919
Total number of elements = 8410
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4

Getting mesh sizing parameters
	Mesh sizing name - leadingEdge
	Mesh sizing name - rootLeadingEdge
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 6181
Number of elements = 6607
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 6607
----------------------------
Total number of nodes    = 6181
Total number of elements = 6607

real	0m13.750s
user	0m23.314s
sys	1m7.411s
+ status=0
+ set +x

=================================================
data/session09/tess_7_MeshSizing.py passed (as expected)
=================================================


=================================================
tess_8_MeshSizing.py test;
+ python tess_8_MeshSizing.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 1655
Number of elements = 3225
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 3225
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 1655
Total number of elements = 3225
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3

Getting mesh sizing parameters
	Mesh sizing name - rootLeadingEdge
	Mesh sizing name - wingSpar1
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 6587
Number of elements = 13200
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 13200
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 6587
Total number of elements = 13200
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3

Getting mesh sizing parameters
	Mesh sizing name - rootLeadingEdge
	Mesh sizing name - wingSpar1
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 22190
Number of elements = 22191
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 22191
----------------------------
Total number of nodes    = 22190
Total number of elements = 22191

real	0m15.144s
user	0m24.278s
sys	1m14.253s
+ status=0
+ set +x

=================================================
data/session09/tess_8_MeshSizing.py passed (as expected)
=================================================


=================================================
tess_MinQuad.py test;
+ python tess_MinQuad.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../../data/ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 299
Number of elements = 387
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 387
----------------------------
Total number of nodes    = 299
Total number of elements = 387
--> Total Elements 387

real	0m10.979s
user	0m18.137s
sys	0m54.094s
+ status=0
+ set +x

=================================================
solutions/session09/tess_MinQuad.py passed (as expected)
=================================================


=================================================
tess_2k.py test;
+ python tess_2k.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../../data/ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3

Getting mesh sizing parameters
	Mesh sizing name - rootLeadingEdge
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 1289
Number of elements = 1189
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 1189
----------------------------
Total number of nodes    = 1289
Total number of elements = 1189
--> Total Elements 1189

real	0m13.556s
user	0m20.635s
sys	1m15.418s
+ status=0
+ set +x

=================================================
solutions/session09/tess_2k.py passed (as expected)
=================================================


=================================================
astros_1_ModalClamped.py test;
+ python astros_1_ModalClamped.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 235
Number of elements = 227
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes    = 235
Total number of elements = 227
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

Getting FEA coordinate systems.......
	Number of coordinate systems - 2
	Coordinate system name - leftWingSkin
	Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 2
	Name = ritePointLoad, index = 1
	Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 4
	Name = upperWing, index = 1
	Name = lowerWing, index = 2
	Name = leftTip, index = 3
	Name = riteTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
	Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 235
	Number of elements = 227
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set

Getting FEA materials.......
	Number of materials - 2
	Material name - Madeupium
	Material name - Unobtainium
	No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 5
	Property name - leftWingSkin
	Property name - riteWingSkin
	Property name - wingRib
	Property name - wingSpar1
	Property name - wingSpar2
	Done getting FEA properties
Updating mesh element types based on properties input

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - rootConstraint
	No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
	No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
	Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Load tuple is NULL - No loads applied
Optimization Control tuple is NULL - Default optimization control is used

Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - EigenAnalysis
	Done getting FEA analyses

Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!!
	Writing analysis cards
	Writing constraint cards--all constraints for each subcase
	Writing material cards
	Writing property cards
	Writing coordinate system cards

==> Running mASTROS...
Reading Astros OUT file - extracting Eigen-Values!
	Number of Eigen-Values = 10
	Loading Eigen-Value = 1
	Loading Eigen-Value = 2
	Loading Eigen-Value = 3
	Loading Eigen-Value = 4
	Loading Eigen-Value = 5
	Loading Eigen-Value = 6
	Loading Eigen-Value = 7
	Loading Eigen-Value = 8
	Loading Eigen-Value = 9
	Loading Eigen-Value = 10

--> Eigen-frequencies:
    1 : 0.0357647
    2 : 0.102451
    3 : 0.102451
    4 : 0.159637
    5 : 0.159637
    6 : 0.215446
    7 : 0.215446
    8 : 0.350115
    9 : 0.350115
    10: 0.466966

real	0m12.736s
user	0m19.520s
sys	1m5.741s
+ status=0
+ set +x

=================================================
data/session10/astros_1_ModalClamped.py passed (as expected)
=================================================


=================================================
astros_2_ModalSupport.py test;
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log
+ python astros_2_ModalSupport.py

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
	Name = ribSupport, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 2)
Getting surface mesh for body 2 (of 2)
Body 1 (of 2)
Number of nodes    = 235
Number of elements = 227
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 227
Body 2 (of 2)
Number of nodes    = 1
Number of elements = 1
Number of node elements          = 1
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 236
Total number of elements = 228
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

Getting FEA coordinate systems.......
	Number of coordinate systems - 2
	Coordinate system name - leftWingSkin
	Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = ribRootPoint, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 2
	Name = ritePointLoad, index = 1
	Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 4
	Name = upperWing, index = 1
	Name = lowerWing, index = 2
	Name = leftTip, index = 3
	Name = riteTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 1
	Name = ribRoot, index = 1
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
	Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
	Name = ribSupport, index = 6
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 235
	Number of elements = 227
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 227
Setting FEA Data
	Mesh for body = 1
	Number of nodal coordinates = 1
	Number of elements = 1
	Elemental Nodes = 1
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 0
Combining multiple FEA meshes!
	Combined Number of nodal coordinates = 236
	Combined Number of elements = 228
	Combined Elemental Nodes = 1
	Combined Elemental Rods  = 0
	Combined Elemental Tria3 = 0
	Combined Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set

Getting FEA materials.......
	Number of materials - 2
	Material name - Madeupium
	Material name - Unobtainium
	No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 6
	Property name - leftWingSkin
	Property name - ribSupport
	Property name - riteWingSkin
	Property name - wingRib
	Property name - wingSpar1
	Property name - wingSpar2
	Done getting FEA properties
Updating mesh element types based on properties input

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - ribRootPoint
	No "constraintType" specified for Constraint tuple ribRootPoint, defaulting to "ZeroDisplacement"
	No "groupName" specified for Constraint tuple ribRootPoint, going to use constraint name
	Done getting FEA constraints

Getting FEA supports.......
	Number of supports - 1
	Support name - ribRootPoint
	No "groupName" specified for Support tuple ribRootPoint, going to use support name
	Done getting FEA supports

Getting FEA connections.......
	Number of connection tuples - 1
	Connection name - ribRoot
	No "groupName" specified for Connection tuple ribRoot!
	Looking for automatic connections from the use of capsConnectLink for ribRoot
	19 automatic connections were made for capsConnect ribRoot (node id 236)
	Done getting FEA connections
Load tuple is NULL - No loads applied
Optimization Control tuple is NULL - Default optimization control is used

Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - EigenAnalysis
	Done getting FEA analyses

Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file

Writing subElement types (if any) - appending mesh file
Writing connection cards - appending mesh file

Writing Astros instruction file....
	Warning: No constraints specified for case EigenAnalysis, assuming all constraints are applied!!!!
	Writing analysis cards
	Writing constraint cards--all constraints for each subcase
	Writing support cards
	Writing material cards
	Writing property cards
	Writing coordinate system cards

==> Running mASTROS...
Reading Astros OUT file - extracting Eigen-Values!
	Number of Eigen-Values = 10
	Loading Eigen-Value = 1
	Loading Eigen-Value = 2
	Loading Eigen-Value = 3
	Loading Eigen-Value = 4
	Loading Eigen-Value = 5
	Loading Eigen-Value = 6
	Loading Eigen-Value = 7
	Loading Eigen-Value = 8
	Loading Eigen-Value = 9
	Loading Eigen-Value = 10

--> Eigen-frequencies:
    1 : 0.0
    2 : 0.0357647
    3 : 0.0365801
    4 : 0.102451
    5 : 0.102453
    6 : 0.159637
    7 : 0.1611
    8 : 0.215446
    9 : 0.215462
    10: 0.350115

real	0m14.900s
user	0m19.852s
sys	0m21.151s
+ status=0
+ set +x

=================================================
data/session10/astros_2_ModalSupport.py passed (as expected)
=================================================


=================================================
astros_3_StaticClamped.py test;
+ python astros_3_StaticClamped.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 235
Number of elements = 227
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes    = 235
Total number of elements = 227
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

Getting FEA coordinate systems.......
	Number of coordinate systems - 2
	Coordinate system name - leftWingSkin
	Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 2
	Name = ritePointLoad, index = 1
	Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 4
	Name = upperWing, index = 1
	Name = lowerWing, index = 2
	Name = leftTip, index = 3
	Name = riteTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
	Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 235
	Number of elements = 227
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set

Getting FEA materials.......
	Number of materials - 2
	Material name - Madeupium
	Material name - Unobtainium
	No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 5
	Property name - leftWingSkin
	Property name - riteWingSkin
	Property name - wingRib
	Property name - wingSpar1
	Property name - wingSpar2
	Done getting FEA properties
Updating mesh element types based on properties input

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - rootConstraint
	No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
	No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
	Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults

Getting FEA loads.......
	Number of loads - 2
	Load name - leftPointLoad
	No "groupName" specified for Load tuple leftPointLoad, going to use load name
	Load name - ritePointLoad
	No "groupName" specified for Load tuple ritePointLoad, going to use load name
	Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used

Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Default
	Done getting FEA analyses

Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint cards--each subcase individually
	Writing load cards
	Writing material cards
	Writing property cards
	Writing coordinate system cards

==> Running mASTROS...

--> Maximum displacements:
--> Tmax 43461.879162311016
--> T1max 738.595
--> T2max 3686.25
--> T3max 43363.8

real	0m11.952s
user	0m19.024s
sys	1m22.809s
+ status=0
+ set +x

=================================================
data/session10/astros_3_StaticClamped.py passed (as expected)
=================================================


=================================================
astros_4_Composite.py test;
+ python astros_4_Composite.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 235
Number of elements = 227
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes    = 235
Total number of elements = 227
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

Getting FEA coordinate systems.......
	Number of coordinate systems - 2
	Coordinate system name - leftWingSkin
	Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 2
	Name = ritePointLoad, index = 1
	Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 4
	Name = upperWing, index = 1
	Name = lowerWing, index = 2
	Name = leftTip, index = 3
	Name = riteTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
	Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 235
	Number of elements = 227
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 227
Aero_Reference value is NULL - No aero reference parameters set

Getting FEA materials.......
	Number of materials - 2
	Material name - Aluminum
	No "materialType" specified for Material tuple Aluminum, defaulting to "Isotropic"
	Material name - Graphite_epoxy
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 5
	Property name - leftWingSkin
	Property name - riteWingSkin
	Property name - wingRib
	Property name - wingSpar1
	Property name - wingSpar2
	Done getting FEA properties
Updating mesh element types based on properties input

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - rootConstraint
	No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
	No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
	Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults

Getting FEA loads.......
	Number of loads - 2
	Load name - leftPointLoad
	No "groupName" specified for Load tuple leftPointLoad, going to use load name
	Load name - ritePointLoad
	No "groupName" specified for Load tuple ritePointLoad, going to use load name
	Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used

Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Default
	Done getting FEA analyses

Writing Astros grid and connectivity file (in large field format) ....
Finished writing Astros grid file

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint cards--each subcase individually
	Writing load cards
	Writing material cards
	Writing property cards
	Writing coordinate system cards

==> Running mASTROS...

--> Maximum displacements:
--> Tmax 12131.654370141774
--> T1max 275.241
--> T2max 1005.74
--> T3max 12103.5

real	0m12.849s
user	0m19.412s
sys	1m8.317s
+ status=0
+ set +x

=================================================
data/session10/astros_4_Composite.py passed (as expected)
=================================================


=================================================
nastran_5_Flutter.py test;
+ python nastran_5_Flutter.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory

==> Running Nastran pre-analysis...
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = Wing, index = 1
	Name = wingSpar2, index = 2
	Name = wingRib, index = 3
	Name = riteWingSkin, index = 4
	Name = wingSpar1, index = 5
	Name = leftWingSkin, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 4)
Getting surface mesh for body 2 (of 4)
Getting surface mesh for body 3 (of 4)
Getting surface mesh for body 4 (of 4)
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Body 1 (of 4)
Number of nodes    = 11
Number of elements = 6
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 6
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Body 2 (of 4)
Number of nodes    = 11
Number of elements = 6
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 6
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Body 3 (of 4)
Number of nodes    = 11
Number of elements = 6
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 6
Body 4 (of 4)
Number of nodes    = 939
Number of elements = 1094
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 1094
----------------------------
Total number of nodes    = 972
Total number of elements = 1112
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

Getting FEA coordinate systems.......
	Number of coordinate systems - 2
	Coordinate system name - leftWingSkin
	Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 2
	Name = ritePointLoad, index = 1
	Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 4
	Name = upperWing, index = 1
	Name = lowerWing, index = 2
	Name = leftTip, index = 3
	Name = riteTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
	Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = Wing, index = 1
	Name = wingSpar2, index = 2
	Name = wingRib, index = 3
	Name = riteWingSkin, index = 4
	Name = wingSpar1, index = 5
	Name = leftWingSkin, index = 6
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 11
	Number of elements = 6
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 6
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Setting FEA Data
	Mesh for body = 1
	Number of nodal coordinates = 11
	Number of elements = 6
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 6
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Setting FEA Data
	Mesh for body = 2
	Number of nodal coordinates = 11
	Number of elements = 6
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 6
Setting FEA Data
	Mesh for body = 3
	Number of nodal coordinates = 939
	Number of elements = 1094
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 1094
Combining multiple FEA meshes!
	Combined Number of nodal coordinates = 972
	Combined Number of elements = 1112
	Combined Elemental Nodes = 0
	Combined Elemental Rods  = 0
	Combined Elemental Tria3 = 0
	Combined Elemental Quad4 = 1112
Getting vortex lattice surface data
	VLM surface name - upperWing
	Done getting vortex lattice surface data

Getting FEA vortex lattice mesh
	Surface 1: Number of points found for aero-spline = 108
	Surface 2: Number of points found for aero-spline = 108

Getting FEA materials.......
	Number of materials - 2
	Material name - Madeupium
	Material name - Unobtainium
	No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 5
	Property name - leftWingSkin
	Property name - riteWingSkin
	Property name - wingRib
	Property name - wingSpar1
	Property name - wingSpar2
	Done getting FEA properties
Updating mesh element types based on properties input

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - rootConstraint
	No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
	No "groupName" specified for Constraint tuple rootConstraint, going to use constraint name
	Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults
Load tuple is NULL - No loads applied
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Design_Equation tuple is NULL - No design equations applied
Design_Table tuple is NULL - No design table constants applied
Design_Opt_Param tuple is NULL - No design optimization parameters applied
Design_Response tuple is NULL - No design responses applied
Design_Equation_Response tuple is NULL - No design equation responses applied

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Flutter
	Done getting FEA analyses

Writing Nastran grid and connectivity file (in large field format) ....
Finished writing Nastran grid file

Writing subElement types (if any) - appending mesh file

Writing Nastran instruction file....
	Warning: No loads specified for case Flutter!!!!
	Writing aero card
	Writing analysis cards
	Writing constraint ADD cards
	Writing constraint cards
	Writing material cards
	Writing property cards
	Writing coordinate system cards
	Writing aeroelastic cards

==> Running Nastran...
sh: 1: nastran: not found

real	0m11.105s
user	0m18.307s
sys	1m4.101s
+ status=0
+ set +x

=================================================
data/session10/nastran_5_Flutter.py passed (as expected)
=================================================


=================================================
aeroelastic_2_Iterative_SU2_Astros.py test;
+ python aeroelastic_2_Iterative_SU2_Astros.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64/CAPS/training/training.log
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory

==> Running SU2 pre-analysis...
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Wing, index = 1
	Name = Farfield, index = 2
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = leftWing, index = 1
	Name = riteWing, index = 2
	Name = Farfield, index = 3

Getting mesh sizing parameters
	Mesh sizing name - Farfield
	Mesh sizing name - leftWing
	Mesh sizing name - riteWing
	Done getting mesh sizing parameters
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.7
AFLR2    : Version Date   07/16/23 @ 01:42PM
AFLR2    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR2    : Compile Date   07/25/23 @ 11:58AM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 11.5.9
AFLR4    : Version Date   08/14/23 @ 12:27AM
AFLR4    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR4    : Compile Date   08/14/23 @ 01:20PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.25
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

EGADS    : EGADS CAD Geometry Setup

EGADS    : Model has 2 Active Bodies

EGADS    : Body 0 is a SolidBody
EGADS    : Body 0 has 1 Shells
EGADS    : Body 0 has 6 Faces
EGADS    : Body 0 has 10 Edges
EGADS    : Body 0 has 6 Loops
EGADS    : Body 0 has 6 Nodes
EGADS    : Body 1 is a SolidBody
EGADS    : Body 1 has 1 Shells
EGADS    : Body 1 has 6 Faces
EGADS    : Body 1 has 12 Edges
EGADS    : Body 1 has 6 Loops
EGADS    : Body 1 has 8 Nodes

EGADS    : Check Grid BCs

EGADS    : Grid BCs are OK

EGADS    : Face Neighbor-Faces Information

EGADS    : QC  = Face Quad Combination Flag
EGADS    : IER = Face Isolated Edge Refinement Flag
EGADS    : ER  = Face Edge Refinement Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.
EGADS    : SF  = Face Scale Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.

EGADS    :   Face          Body    QC   IER       ER    Scale   Neighbor
EGADS    :     ID  Active    ID  Flag  Flag   Weight   Factor   Faces
EGADS    :      1     Yes     0     0     1        1        1   2 3 4
EGADS    :      2     Yes     0     0     1        1        1   1 3 5
EGADS    :      3     Yes     0     0     1        1        1   1 2
EGADS    :      4     Yes     0     0     1        1        1   1 5 6
EGADS    :      5     Yes     0     0     1        1        1   2 4 6
EGADS    :      6     Yes     0     0     1        1        1   4 5
EGADS    :      7     Yes     1     0     1       NA       NA   9 10 11 12
EGADS    :      8     Yes     1     0     1       NA       NA   9 10 11 12
EGADS    :      9     Yes     1     0     1       NA       NA   7 8 11 12
EGADS    :     10     Yes     1     0     1       NA       NA   7 8 11 12
EGADS    :     11     Yes     1     0     1       NA       NA   7 8 9 10
EGADS    :     12     Yes     1     0     1       NA       NA   7 8 9 10

EGADS    : Face Edges Information

EGADS    :   Face   Edges
EGADS    :      1   -1 2 3 -4
EGADS    :      2   -3 5 1 -6
EGADS    :      3   4 6
EGADS    :      4   7 9 -8 -2
EGADS    :      5   8 10 -7 -5
EGADS    :      6   -9 -10
EGADS    :      7   11 12 -13 -14
EGADS    :      8   -15 18 17 -16
EGADS    :      9   19 15 -20 -11
EGADS    :     10   -21 13 22 -17
EGADS    :     11   14 21 -18 -19
EGADS    :     12   -12 20 16 -22

EGADS    : Face Loops Information

EGADS    :   Face   Loops
EGADS    :      1   1
EGADS    :      2   2
EGADS    :      3   3
EGADS    :      4   4
EGADS    :      5   5
EGADS    :      6   6
EGADS    :      7   7
EGADS    :      8   8
EGADS    :      9   9
EGADS    :     10   10
EGADS    :     11   11
EGADS    :     12   12

EGADS    : Loop Edges Information

EGADS    :   Loop  Active Sense   Edges
EGADS    :      1     Yes     1   -1 2 3 -4
EGADS    :      2     Yes     1   -3 5 1 -6
EGADS    :      3     Yes     1   4 6
EGADS    :      4     Yes     1   7 9 -8 -2
EGADS    :      5     Yes     1   8 10 -7 -5
EGADS    :      6     Yes     1   -9 -10
EGADS    :      7     Yes     1   11 12 -13 -14
EGADS    :      8     Yes     1   -15 18 17 -16
EGADS    :      9     Yes     1   19 15 -20 -11
EGADS    :     10     Yes     1   -21 13 22 -17
EGADS    :     11     Yes     1   14 21 -18 -19
EGADS    :     12     Yes     1   -12 20 16 -22

EGADS    : Edge Node, Scale Factor, and Neighbor-Faces Information

EGADS    : ESF = Edge Scale Factor
EGADS    :       Not applicable for DEGENERATE Edges or Edges with a FarField
EGADS    :       Grid BC Neighbor Face.

EGADS    :                                             Neighbor
EGADS    :   Edge  Body  Active Node1 Node2      ESF   Faces
EGADS    :      1     0     Yes     1     2        1   1 2
EGADS    :      2     0     Yes     1     3        1   1 4
EGADS    :      3     0     Yes     3     4        1   1 2
EGADS    :      4     0     Yes     2     4        1   1 3
EGADS    :      5     0     Yes     3     1        1   2 5
EGADS    :      6     0     Yes     4     2        1   2 3
EGADS    :      7     0     Yes     1     5        1   4 5
EGADS    :      8     0     Yes     3     6        1   4 5
EGADS    :      9     0     Yes     5     6        1   4 6
EGADS    :     10     0     Yes     6     5        1   5 6
EGADS    :     11     1     Yes     8     7       NA   7 9
EGADS    :     12     1     Yes     7     9       NA   7 12
EGADS    :     13     1     Yes    10     9       NA   7 10
EGADS    :     14     1     Yes     8    10       NA   7 11
EGADS    :     15     1     Yes    12    11       NA   8 9
EGADS    :     16     1     Yes    11    13       NA   8 12
EGADS    :     17     1     Yes    14    13       NA   8 10
EGADS    :     18     1     Yes    12    14       NA   8 11
EGADS    :     19     1     Yes     8    12       NA   9 11
EGADS    :     20     1     Yes     7    11       NA   9 12
EGADS    :     21     1     Yes    10    14       NA   10 11
EGADS    :     22     1     Yes     9    13       NA   10 12

EGADS    : Node Information

EGADS    :   Node  Active      Coordinates
EGADS    :      1     Yes       1.61374306                0                0
EGADS    :      2     Yes       2.37421202                0      0.355213563
EGADS    :      3     Yes                0                0                0
EGADS    :      4     Yes       1.40965066                0      0.270825378
EGADS    :      5     Yes       2.37421202       3.87298335      0.355213563
EGADS    :      6     Yes       1.40965066       3.87298335      0.270825378
EGADS    :      7     Yes                0                0       77.6430368
EGADS    :      8     Yes                0                0                0
EGADS    :      9     Yes                0       77.4596689       77.6430368
EGADS    :     10     Yes                0       77.4596689                0
EGADS    :     11     Yes       78.6462641                0       77.6430368
EGADS    :     12     Yes       78.6462641                0                0
EGADS    :     13     Yes       78.6462641       77.4596689       77.6430368
EGADS    :     14     Yes       78.6462641       77.4596689                0

EGADS    : Face and Edge Match Information

EGADS    : No Face Matches Found

AFLR4    : Surface Mesh Spacing Setup

AFLR4    : Max Bounding Box Length     = 154.919
AFLR4    : Min Bounding Box Length     = 154.919
AFLR4    : Max Ref Bounding Box Length = 7.74597
AFLR4    : Min Ref Bounding Box Length = 0.433058
AFLR4    : Reference Length            = 6.45497
AFLR4    : BL Thickness                = 0
AFLR4    : FarField Spacing            = 21.0478
AFLR4    : Abs Min Surf Spacing        = 0.0161374
AFLR4    : Min Surf Spacing            = 0.0322749
AFLR4    : Max Surf Spacing            = 0.645497
AFLR4    : Global Scale Factor         = 1

AFLR4    : Geometry Definition Information

AFLR4    : Definition              Definition   Composite             Grid BC
AFLR4    :         ID                    Type          ID                Type
AFLR4    :          0     glue-only composite           -                   -
AFLR4    :          1            CAD geometry           0            STD w/BL
AFLR4    :          2            CAD geometry           0            STD w/BL
AFLR4    :          3            CAD geometry           0            STD w/BL
AFLR4    :          4            CAD geometry           0            STD w/BL
AFLR4    :          5            CAD geometry           0            STD w/BL
AFLR4    :          6            CAD geometry           0            STD w/BL
AFLR4    :          7            CAD geometry           0            FARFIELD
AFLR4    :          8            CAD geometry           0            FARFIELD
AFLR4    :          9            CAD geometry           0            FARFIELD
AFLR4    :         10            CAD geometry           0            FARFIELD
AFLR4    :         11            CAD geometry           0            FARFIELD
AFLR4    :         12            CAD geometry           0            FARFIELD

AFLR4    : Define CAD surface definition 1
AFLR4    : Define CAD surface definition 2
AFLR4    : Define CAD surface definition 3
AFLR4    : Define CAD surface definition 4
AFLR4    : Define CAD surface definition 5
AFLR4    : Define CAD surface definition 6
AFLR4    : Define CAD surface definition 7
AFLR4    : Define CAD surface definition 8
AFLR4    : Define CAD surface definition 9
AFLR4    : Define CAD surface definition 10
AFLR4    : Define CAD surface definition 11
AFLR4    : Define CAD surface definition 12

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Trias,Quads=      1658      3135         0
AFLR4    : Nodes, Trias,Quads=       971      1761         0

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Trias,Quads=      1628      3077         0
AFLR4    : Nodes, Trias,Quads=       941      1703         0

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Trias,Quads=        48        65         0
AFLR4    : Nodes, Trias,Quads=        44        57         0

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Trias,Quads=      1668      3155         0
AFLR4    : Nodes, Trias,Quads=       986      1791         0

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Trias,Quads=      1625      3071         0
AFLR4    : Nodes, Trias,Quads=       930      1681         0

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Trias,Quads=        48        65         0
AFLR4    : Nodes, Trias,Quads=        44        57         0

AFLR4    : Generate optimal mesh on surface definition 7
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 8
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 9
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 10
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 11
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 12
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      3847      7686       938

AFLR4    : Curvature BG Surface Grid Generation

AFLR4    : Nodes, Faces      =      3847      7686

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Trias,Quads=      3367      6423         0
AFLR4    : Nodes, Trias,Quads=      2401      4491         0

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Trias,Quads=      3394      6478         0
AFLR4    : Nodes, Trias,Quads=      2282      4254         0

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Trias,Quads=       145       226         0
AFLR4    : Nodes, Trias,Quads=       131       198         0

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Trias,Quads=      3366      6421         0
AFLR4    : Nodes, Trias,Quads=      2394      4477         0

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Trias,Quads=      3405      6500         0
AFLR4    : Nodes, Trias,Quads=      2289      4268         0

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Trias,Quads=       145       226         0
AFLR4    : Nodes, Trias,Quads=       131       198         0

AFLR4    : Generate optimal mesh on surface definition 7
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 8
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 9
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 10
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 11
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

AFLR4    : Generate optimal mesh on surface definition 12
AFLR2    : Nodes, Trias,Quads=        73       116         0
AFLR4    : Nodes, Trias,Quads=        68       106         0

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      9265     18522      1526

OVERALL  : CPU Time          =     0.352   seconds
Body 1 (of 2)
Number of nodes    = 8945
Number of elements = 17886
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17886
Number of quadrilateral elements = 0
Body 2 (of 2)
Number of nodes    = 320
Number of elements = 636
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 636
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 9265
Total number of elements = 18522
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = leftWing, index = 1
	Name = riteWing, index = 2
	Name = Farfield, index = 3
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Wing, index = 1
	Name = Farfield, index = 2
Getting volume mesh
 
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
 
UG PARAM : mrecm                       = 3         
UG PARAM : mrecqm                      = 3         
UG PARAM : mpfrmt                      = 0         
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.7
AFLR2    : Version Date   07/16/23 @ 01:42PM
AFLR2    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR2    : Compile Date   07/25/23 @ 11:58AM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 11.5.9
AFLR4    : Version Date   08/14/23 @ 12:27AM
AFLR4    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR4    : Compile Date   08/14/23 @ 01:20PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.25
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

EGADS    : EGADS CAD Geometry Setup

EGADS    : Model has 2 Active Bodies

EGADS    : Body 0 is a SolidBody
EGADS    : Body 0 has 1 Shells
EGADS    : Body 0 has 6 Faces
EGADS    : Body 0 has 10 Edges
EGADS    : Body 0 has 6 Loops
EGADS    : Body 0 has 6 Nodes
EGADS    : Body 1 is a SolidBody
EGADS    : Body 1 has 1 Shells
EGADS    : Body 1 has 6 Faces
EGADS    : Body 1 has 12 Edges
EGADS    : Body 1 has 6 Loops
EGADS    : Body 1 has 8 Nodes

EGADS    : Check Grid BCs

EGADS    : Grid BCs are OK

EGADS    : Face Neighbor-Faces Information

EGADS    : QC  = Face Quad Combination Flag
EGADS    : IER = Face Isolated Edge Refinement Flag
EGADS    : ER  = Face Edge Refinement Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.
EGADS    : SF  = Face Scale Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.

EGADS    :   Face          Body    QC   IER       ER    Scale   Neighbor
EGADS    :     ID  Active    ID  Flag  Flag   Weight   Factor   Faces
EGADS    :      1     Yes     0     0     1        1        1   2 3 4
EGADS    :      2     Yes     0     0     1        1        1   1 3 5
EGADS    :      3     Yes     0     0     1        1        1   1 2
EGADS    :      4     Yes     0     0     1        1        1   1 5 6
EGADS    :      5     Yes     0     0     1        1        1   2 4 6
EGADS    :      6     Yes     0     0     1        1        1   4 5
EGADS    :      7     Yes     1     0     1       NA       NA   9 10 11 12
EGADS    :      8     Yes     1     0     1       NA       NA   9 10 11 12
EGADS    :      9     Yes     1     0     1       NA       NA   7 8 11 12
EGADS    :     10     Yes     1     0     1       NA       NA   7 8 11 12
EGADS    :     11     Yes     1     0     1       NA       NA   7 8 9 10
EGADS    :     12     Yes     1     0     1       NA       NA   7 8 9 10

EGADS    : Face Edges Information

EGADS    :   Face   Edges
EGADS    :      1   -1 2 3 -4
EGADS    :      2   -3 5 1 -6
EGADS    :      3   4 6
EGADS    :      4   7 9 -8 -2
EGADS    :      5   8 10 -7 -5
EGADS    :      6   -9 -10
EGADS    :      7   11 12 -13 -14
EGADS    :      8   -15 18 17 -16
EGADS    :      9   19 15 -20 -11
EGADS    :     10   -21 13 22 -17
EGADS    :     11   14 21 -18 -19
EGADS    :     12   -12 20 16 -22

EGADS    : Face Loops Information

EGADS    :   Face   Loops
EGADS    :      1   1
EGADS    :      2   2
EGADS    :      3   3
EGADS    :      4   4
EGADS    :      5   5
EGADS    :      6   6
EGADS    :      7   7
EGADS    :      8   8
EGADS    :      9   9
EGADS    :     10   10
EGADS    :     11   11
EGADS    :     12   12

EGADS    : Loop Edges Information

EGADS    :   Loop  Active Sense   Edges
EGADS    :      1     Yes     1   -1 2 3 -4
EGADS    :      2     Yes     1   -3 5 1 -6
EGADS    :      3     Yes     1   4 6
EGADS    :      4     Yes     1   7 9 -8 -2
EGADS    :      5     Yes     1   8 10 -7 -5
EGADS    :      6     Yes     1   -9 -10
EGADS    :      7     Yes     1   11 12 -13 -14
EGADS    :      8     Yes     1   -15 18 17 -16
EGADS    :      9     Yes     1   19 15 -20 -11
EGADS    :     10     Yes     1   -21 13 22 -17
EGADS    :     11     Yes     1   14 21 -18 -19
EGADS    :     12     Yes     1   -12 20 16 -22

EGADS    : Edge Node, Scale Factor, and Neighbor-Faces Information

EGADS    : ESF = Edge Scale Factor
EGADS    :       Not applicable for DEGENERATE Edges or Edges with a FarField
EGADS    :       Grid BC Neighbor Face.

EGADS    :                                             Neighbor
EGADS    :   Edge  Body  Active Node1 Node2      ESF   Faces
EGADS    :      1     0     Yes     1     2        1   1 2
EGADS    :      2     0     Yes     1     3        1   1 4
EGADS    :      3     0     Yes     3     4        1   1 2
EGADS    :      4     0     Yes     2     4        1   1 3
EGADS    :      5     0     Yes     3     1        1   2 5
EGADS    :      6     0     Yes     4     2        1   2 3
EGADS    :      7     0     Yes     1     5        1   4 5
EGADS    :      8     0     Yes     3     6        1   4 5
EGADS    :      9     0     Yes     5     6        1   4 6
EGADS    :     10     0     Yes     6     5        1   5 6
EGADS    :     11     1     Yes     8     7       NA   7 9
EGADS    :     12     1     Yes     7     9       NA   7 12
EGADS    :     13     1     Yes    10     9       NA   7 10
EGADS    :     14     1     Yes     8    10       NA   7 11
EGADS    :     15     1     Yes    12    11       NA   8 9
EGADS    :     16     1     Yes    11    13       NA   8 12
EGADS    :     17     1     Yes    14    13       NA   8 10
EGADS    :     18     1     Yes    12    14       NA   8 11
EGADS    :     19     1     Yes     8    12       NA   9 11
EGADS    :     20     1     Yes     7    11       NA   9 12
EGADS    :     21     1     Yes    10    14       NA   10 11
EGADS    :     22     1     Yes     9    13       NA   10 12

EGADS    : Node Information

EGADS    :   Node  Active      Coordinates
EGADS    :      1     Yes       1.61374306                0                0
EGADS    :      2     Yes       2.37421202                0      0.355213563
EGADS    :      3     Yes                0                0                0
EGADS    :      4     Yes       1.40965066                0      0.270825378
EGADS    :      5     Yes       2.37421202       3.87298335      0.355213563
EGADS    :      6     Yes       1.40965066       3.87298335      0.270825378
EGADS    :      7     Yes                0                0       77.6430368
EGADS    :      8     Yes                0                0                0
EGADS    :      9     Yes                0       77.4596689       77.6430368
EGADS    :     10     Yes                0       77.4596689                0
EGADS    :     11     Yes       78.6462641                0       77.6430368
EGADS    :     12     Yes       78.6462641                0                0
EGADS    :     13     Yes       78.6462641       77.4596689       77.6430368
EGADS    :     14     Yes       78.6462641       77.4596689                0

EGADS    : Face and Edge Match Information

EGADS    : No Face Matches Found

AFLR4    : Surface Mesh Spacing Setup

AFLR4    : Max Bounding Box Length     = 154.919
AFLR4    : Min Bounding Box Length     = 154.919
AFLR4    : Max Ref Bounding Box Length = 7.74597
AFLR4    : Min Ref Bounding Box Length = 0.433058
AFLR4    : Reference Length            = 0.433058
AFLR4    : BL Thickness                = 0
AFLR4    : FarField Spacing            = 16.9832
AFLR4    : Abs Min Surf Spacing        = 0.00108265
AFLR4    : Min Surf Spacing            = 0.00216529
AFLR4    : Max Surf Spacing            = 0.0433058
AFLR4    : Global Scale Factor         = 1

AFLR4    : Geometry Definition Information

AFLR4    : Definition              Definition   Composite             Grid BC
AFLR4    :         ID                    Type          ID                Type
AFLR4    :          0     glue-only composite           -                   -
AFLR4    :          1            CAD geometry           0                 STD
AFLR4    :          2            CAD geometry           0                 STD
AFLR4    :          3            CAD geometry           0                 STD
AFLR4    :          4            CAD geometry           0                 STD
AFLR4    :          5            CAD geometry           0                 STD
AFLR4    :          6            CAD geometry           0                 STD
AFLR4    :          7            CAD geometry           0            FARFIELD
AFLR4    :          8            CAD geometry           0            FARFIELD
AFLR4    :          9            CAD geometry           0            FARFIELD
AFLR4    :         10            CAD geometry           0            FARFIELD
AFLR4    :         11            CAD geometry           0            FARFIELD
AFLR4    :         12            CAD geometry           0            FARFIELD

AFLR4    : Define CAD surface definition 1
AFLR4    : Define CAD surface definition 2
AFLR4    : Define CAD surface definition 3
AFLR4    : Define CAD surface definition 4
AFLR4    : Define CAD surface definition 5
AFLR4    : Define CAD surface definition 6
AFLR4    : Define CAD surface definition 7
AFLR4    : Define CAD surface definition 8
AFLR4    : Define CAD surface definition 9
AFLR4    : Define CAD surface definition 10
AFLR4    : Define CAD surface definition 11
AFLR4    : Define CAD surface definition 12
 
AFLR43   : INPUT SURFACE MESH FROM TESS
 
AFLR43   : Quad Surface Faces=         0
AFLR43   : Tria Surface Faces=     18522
AFLR43   : Nodes             =      9265
 
 
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
 
UG PARAM : mrecm                       = 3         
UG PARAM : mrecqm                      = 3         
UG PARAM : mpfrmt                      = 0         
 
AFLR3    : ---------------------------------------
AFLR3    : AFLR3 LIBRARY
AFLR3    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR3    : TETRAHEDRAL GRID GENERATOR
AFLR3    : Version Number 16.32.49
AFLR3    : Version Date   07/26/23 @ 12:32AM
AFLR3    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR3    : Compile Date   07/26/23 @ 01:49PM
AFLR3    : Copyright 1994-2021, D.L. Marcum
AFLR3    : ---------------------------------------
 
AFLR3 IC : INPUT SURFACE GRID CHECK
 
AFLR3 IC : Nodes, Elements   =      9265         0

UG3      : Boundary Conditions

UG3      :  B-Face ID            Boundary Condition
UG3      :          1                         Solid
UG3      :          2                         Solid
UG3      :          3                         Solid
UG3      :          4                         Solid
UG3      :          5                         Solid
UG3      :          6                         Solid
UG3      :          7                      FarField
UG3      :          8                      FarField
UG3      :          9                      FarField
UG3      :         10                      FarField
UG3      :         11                      FarField
UG3      :         12                      FarField
 
AFLR3    : CPU Time          =     0.029   seconds
 
AFLR3 IG : INITIAL VOLUME GRID GENERATION
 
AFLR3 IG : Nodes, Elements   =      9265         0
AFLR3 IG : Nodes, Elements   =         8        10
AFLR3 IG : Nodes, Elements   =      1854     12666
AFLR3 IG : Nodes, Elements   =      3708     26130
AFLR3 IG : Nodes, Elements   =      5562     39589
AFLR3 IG : Nodes, Elements   =      7416     54244
AFLR3 IG : Nodes, Elements   =      9270     69463
AFLR3 IG : Nodes, Elements   =      9272     69530
AFLR3 IG : Nodes, Elements   =      9272     69335
AFLR3 IG : Nodes, Elements   =      9265     42285
AFLR3 IG : Nodes, Elements   =      9265     42353
AFLR3 IG : Nodes, Elements   =      9265     30496
AFLR3 IG : Nodes, Elements   =      9265     28301
 
AFLR3    : CPU Time          =     0.429   seconds
 
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
 
AFLR3 GG : Nodes, Elements   =      9265     28301
AFLR3 GG : Nodes, Elements   =     13542     41195
AFLR3 GG : Nodes, Elements   =     13542     58908
AFLR3 GG : Nodes, Elements   =     13542     54250
AFLR3 GG : Nodes, Elements   =     17058     65245
AFLR3 GG : Nodes, Elements   =     17058     78728
AFLR3 GG : Nodes, Elements   =     17058     74303
AFLR3 GG : Nodes, Elements   =     20605     85295
AFLR3 GG : Nodes, Elements   =     20605     99195
AFLR3 GG : Nodes, Elements   =     20605     94904
AFLR3 GG : Nodes, Elements   =     24311    106150
AFLR3 GG : Nodes, Elements   =     24311    121010
AFLR3 GG : Nodes, Elements   =     24311    116688
AFLR3 GG : Nodes, Elements   =     28109    128222
AFLR3 GG : Nodes, Elements   =     28109    143116
AFLR3 GG : Nodes, Elements   =     28109    139085
AFLR3 GG : Nodes, Elements   =     31833    150343
AFLR3 GG : Nodes, Elements   =     31833    164956
AFLR3 GG : Nodes, Elements   =     31833    161115
AFLR3 GG : Nodes, Elements   =     35425    171944
AFLR3 GG : Nodes, Elements   =     35425    186053
AFLR3 GG : Nodes, Elements   =     35425    182380
AFLR3 GG : Nodes, Elements   =     38915    192902
AFLR3 GG : Nodes, Elements   =     38915    206546
AFLR3 GG : Nodes, Elements   =     38915    203031
AFLR3 GG : Nodes, Elements   =     42279    213161
AFLR3 GG : Nodes, Elements   =     42279    226492
AFLR3 GG : Nodes, Elements   =     42279    223051
AFLR3 GG : Nodes, Elements   =     45563    232931
AFLR3 GG : Nodes, Elements   =     45563    245768
AFLR3 GG : Nodes, Elements   =     45563    242514
AFLR3 GG : Nodes, Elements   =     48695    251935
AFLR3 GG : Nodes, Elements   =     48695    264207
AFLR3 GG : Nodes, Elements   =     48695    261088
AFLR3 GG : Nodes, Elements   =     51591    269788
AFLR3 GG : Nodes, Elements   =     51591    281183
AFLR3 GG : Nodes, Elements   =     51591    278253
AFLR3 GG : Nodes, Elements   =     54386    286650
AFLR3 GG : Nodes, Elements   =     54386    297696
AFLR3 GG : Nodes, Elements   =     54386    294892
AFLR3 GG : Nodes, Elements   =     57084    303004
AFLR3 GG : Nodes, Elements   =     57084    313644
AFLR3 GG : Nodes, Elements   =     57084    310937
AFLR3 GG : Nodes, Elements   =     59614    318534
AFLR3 GG : Nodes, Elements   =     59614    328459
AFLR3 GG : Nodes, Elements   =     59614    326028
AFLR3 GG : Nodes, Elements   =     61932    332987
AFLR3 GG : Nodes, Elements   =     61932    342053
AFLR3 GG : Nodes, Elements   =     61932    339758
AFLR3 GG : Nodes, Elements   =     64173    346486
AFLR3 GG : Nodes, Elements   =     64173    355203
AFLR3 GG : Nodes, Elements   =     64173    353091
AFLR3 GG : Nodes, Elements   =     66220    359236
AFLR3 GG : Nodes, Elements   =     66220    367234
AFLR3 GG : Nodes, Elements   =     66220    365224
AFLR3 GG : Nodes, Elements   =     68183    371120
AFLR3 GG : Nodes, Elements   =     68183    378771
AFLR3 GG : Nodes, Elements   =     68183    376893
AFLR3 GG : Nodes, Elements   =     70021    382413
AFLR3 GG : Nodes, Elements   =     70021    389635
AFLR3 GG : Nodes, Elements   =     70021    387894
AFLR3 GG : Nodes, Elements   =     71738    393050
AFLR3 GG : Nodes, Elements   =     71738    399670
AFLR3 GG : Nodes, Elements   =     71738    398113
AFLR3 GG : Nodes, Elements   =     73289    402770
AFLR3 GG : Nodes, Elements   =     73289    408828
AFLR3 GG : Nodes, Elements   =     73289    407358
AFLR3 GG : Nodes, Elements   =     74785    411846
AFLR3 GG : Nodes, Elements   =     74785    417552
AFLR3 GG : Nodes, Elements   =     74785    416226
AFLR3 GG : Nodes, Elements   =     76147    420314
AFLR3 GG : Nodes, Elements   =     76147    425638
AFLR3 GG : Nodes, Elements   =     76147    424379
AFLR3 GG : Nodes, Elements   =     77386    428096
AFLR3 GG : Nodes, Elements   =     77386    432940
AFLR3 GG : Nodes, Elements   =     77386    431774
AFLR3 GG : Nodes, Elements   =     78483    435067
AFLR3 GG : Nodes, Elements   =     78483    439378
AFLR3 GG : Nodes, Elements   =     78483    438266
AFLR3 GG : Nodes, Elements   =     79434    441119
AFLR3 GG : Nodes, Elements   =     79434    444842
AFLR3 GG : Nodes, Elements   =     79434    443913
AFLR3 GG : Nodes, Elements   =     80223    446281
AFLR3 GG : Nodes, Elements   =     80223    449423
AFLR3 GG : Nodes, Elements   =     80223    448600
AFLR3 GG : Nodes, Elements   =     80840    450451
AFLR3 GG : Nodes, Elements   =     80840    452964
AFLR3 GG : Nodes, Elements   =     80840    452292
AFLR3 GG : Nodes, Elements   =     81284    453624
AFLR3 GG : Nodes, Elements   =     81284    455393
AFLR3 GG : Nodes, Elements   =     81284    454894
AFLR3 GG : Nodes, Elements   =     81599    455839
AFLR3 GG : Nodes, Elements   =     81599    457118
AFLR3 GG : Nodes, Elements   =     81599    456750
AFLR3 GG : Nodes, Elements   =     81779    457290
AFLR3 GG : Nodes, Elements   =     81779    458010
AFLR3 GG : Nodes, Elements   =     81779    457813
AFLR3 GG : Nodes, Elements   =     81888    458140
AFLR3 GG : Nodes, Elements   =     81888    458622
AFLR3 GG : Nodes, Elements   =     81888    458452
AFLR3 GG : Nodes, Elements   =     81937    458599
AFLR3 GG : Nodes, Elements   =     81937    458810
AFLR3 GG : Nodes, Elements   =     81937    458739
AFLR3 GG : Nodes, Elements   =     81953    458787
AFLR3 GG : Nodes, Elements   =     81953    458858
AFLR3 GG : Nodes, Elements   =     81953    458828
AFLR3 GG : Nodes, Elements   =     81961    458852
AFLR3 GG : Nodes, Elements   =     81961    458887
AFLR3 GG : Nodes, Elements   =     81961    458871
AFLR3 GG : Nodes, Elements   =     81966    458886
AFLR3 GG : Nodes, Elements   =     81966    458898
AFLR3 GG : Nodes, Elements   =     81966    458893
AFLR3 GG : Nodes, Elements   =     81968    458899
AFLR3 GG : Nodes, Elements   =     81968    458905
AFLR3 GG : Nodes, Elements   =     81968    458903
 
AFLR3    : CPU Time          =     7.493   seconds
 
AFLR3 QI : QUALITY IMPROVEMENT
 
AFLR3 QI : Nodes, Elements   =     81968    458903
AFLR3 QI : Nodes, Elements   =     81513    456317
AFLR3 QI : Nodes, Elements   =     81426    455827
AFLR3 QI : Nodes, Elements   =     81418    455777
AFLR3 QI : Nodes, Elements   =     81416    455768
AFLR3 QI : Nodes, Elements   =     81416    457723
AFLR3 QI : Nodes, Elements   =     81416    455611
AFLR3 QI : Nodes, Elements   =     81416    454711
AFLR3 QI : Nodes, Elements   =     81416    454979
AFLR3 QI : Nodes, Elements   =     81416    454537
AFLR3 QI : Nodes, Elements   =     81416    454422
 
AFLR3    : CPU Time          =     1.817   seconds
 
AFLR3    : DONE

UG3      : DIHEDRAL ANGLE CHECK

UG3      : No. Tet Elems     =    454422
UG3      : Min, Max Ang      =     12.41     159.2
UG3      : Average Angle     =      70.2
UG3      : No. Angle>160.0   =         0
UG3      : No. Angle>179.9   =         0

UG3      : VOL CHECK

UG3      : Total-Volume      =  3.72e+06

UG3      : No. Tet Elems     =    454422
UG3      : Min Vol           =  1.01e-06
UG3      : Average Vol       =      8.18
UG3      : Total-Tet-Vol     =  3.72e+06
UG3      : No. Vol<TOL       =         0

UG3      : Q VOL-LENGTH-RATIO CHECK
                      2/3        2
UG3      : Q = c * Vol   / sum( L  )
UG3      : 0 <= Q <= 1

UG3      : No. Tet Elems     =    454422
UG3      : Min, Max Q        =     0.205         1
UG3      : Average Q         =     0.896
UG3      : No. Q<       0.1  =         0
UG3      : No. Q<      0.01  =         0

OVERALL  : CPU Time          =     9.944   seconds

UG3      : DIHEDRAL ANGLE CHECK

UG3      : No. Tet Elems     =    454422
UG3      : Min, Max Ang      =     12.41     159.2
UG3      : Average Angle     =      70.2
UG3      : No. Angle>160.0   =         0
UG3      : No. Angle>179.9   =         0

UG3      : VOL CHECK

UG3      : Total-Volume      =  3.72e+06

UG3      : No. Tet Elems     =    454422
UG3      : Min Vol           =  1.01e-06
UG3      : Average Vol       =      8.18
UG3      : Total-Tet-Vol     =  3.72e+06
UG3      : No. Vol<TOL       =         0

UG3      : Q VOL-LENGTH-RATIO CHECK
                      2/3        2
UG3      : Q = c * Vol   / sum( L  )
UG3      : 0 <= Q <= 1
UG3      : Note that L includes scaling for BL-aspect=ratio

UG3      : No. Tet Elems     =    454422
UG3      : Min, Max Q        =     0.361         1
UG3      : Average Q         =     0.863
UG3      : No. Q<       0.1  =         0
UG3      : No. Q<      0.01  =         0

UG3      : CPU Time          =     0.000   seconds

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.25
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

EGADS    : CREATE EGADS TESS FROM AFLR3 DATA

EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 1
EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 2
EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 3
EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 4
EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 5
EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 6
EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 7
EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 8
EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 9
EGADS    : CREATING TESSELLATION FOR BODY 0 EDGE 10

EGADS    : CREATING TESSELLATION FOR BODY 0 FACE 1
EGADS    : CREATING TESSELLATION FOR BODY 0 FACE 2
EGADS    : CREATING TESSELLATION FOR BODY 0 FACE 3
EGADS    : CREATING TESSELLATION FOR BODY 0 FACE 4
EGADS    : CREATING TESSELLATION FOR BODY 0 FACE 5
EGADS    : CREATING TESSELLATION FOR BODY 0 FACE 6

EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 11
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 12
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 13
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 14
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 15
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 16
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 17
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 18
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 19
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 20
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 21
EGADS    : CREATING TESSELLATION FOR BODY 1 EDGE 22

EGADS    : CREATING TESSELLATION FOR BODY 1 FACE 7
EGADS    : CREATING TESSELLATION FOR BODY 1 FACE 8
EGADS    : CREATING TESSELLATION FOR BODY 1 FACE 9
EGADS    : CREATING TESSELLATION FOR BODY 1 FACE 10
EGADS    : CREATING TESSELLATION FOR BODY 1 FACE 11
EGADS    : CREATING TESSELLATION FOR BODY 1 FACE 12

EGADS    : EGADS TESS CREATED

EGADS    : CHECK TESS FACE NODE MAP

EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 1
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 2
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 3
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 4
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 5
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 6
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 7
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 8
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 9
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 10
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 11
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 12
Volume mesh:
	Number of nodes          = 81416
	Number of elements       = 472944
	Number of triangles      = 18522
	Number of quadrilatarals = 0
	Number of tetrahedrals   = 454422
	Number of pyramids       = 0
	Number of prisms         = 0
	Number of hexahedrals    = 0
No project name ("Proj_Name") provided - A volume mesh will not be written out

Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Farfield
	Boundary condition name - Wing
	Done getting CFD boundary conditions
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.5.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 10 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 7.74597 m.
Reference origin for moment evaluation is (0.322749, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.

Surface(s) plotted in the output file: BC_1.
Surface(s) affected by the design variables: BC_1.
Input mesh file name: ../aflr3/aflr3_0.su2

--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1. 
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.

--------------- Time Numerical Integration  ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------ Convergence Criteria  ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface file name: surface_flow_aeroelasticIterative.
Volume file name: flow_aeroelasticIterative.
Restart file name: restart_flow_aeroelasticIterative.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_1|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_2|
+-----------------------------------------------------------------------+

-------------------- Output Preprocessing ( Zone 0 ) --------------------

WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)

Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
81416 grid points.
454422 volume elements.
2 surface markers.
17886 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
454422 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 3.71806e+06.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 431.689. Mean K: 20.6913. Standard deviation K: 49.4454.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        51.1523|        86.7063|
|     CV Face Area Aspect Ratio|        1.04012|        115.282|
|           CV Sub-Volume Ratio|              1|        701.712|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     81416|    1/1.00|        10|
|         1|     13392|    1/6.08|    8.2187|
|         2|      2069|    1/6.47|   6.61504|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5583 m^2.
Area projection in the x-plane = 1.52985 m^2, y-plane = 0.868532 m^2, z-plane = 9.83638 m^2.
Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399868 m.
Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0329598 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.

-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

------------------- Numerics Preprocessing ( Zone 0 ) -------------------

----------------- Integration Preprocessing ( Zone 0 ) ------------------

------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.

------------------------------ Begin Solver -----------------------------

Simulation Run using the Single-zone Driver
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  4.2672e+00|   -1.762880|    0.455100|    0.055818|    3.706226|   -0.552238|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  4.1116e+00|   -1.567620|    0.800265|    0.530357|    3.903824|   -0.295493|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  4.0862e+00|   -1.601362|    0.945584|    0.763508|    3.871421|    1.801614|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  4.1220e+00|   -1.681553|    0.931856|    0.796718|    3.784455|   -8.276542|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  4.2194e+00|   -1.622632|    0.831000|    0.682309|    3.844421|   -5.286333|

----------------------------- Solver Exit -------------------------------

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.62263|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticIterative.dat|

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|CSV file                           |surface_flow_aeroelasticIterative.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary                     |flow_aeroelasticIterative.szplt    |

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary surface             |surface_flow_aeroelasticIterative.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
+-----------------------------------------------------------------------+

--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


==> Running SU2 post-analysis...

==> Running ASTROS pre-analysis...
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 265
Number of elements = 346
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 346
----------------------------
Total number of nodes    = 265
Total number of elements = 346
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

Getting FEA coordinate systems.......
	Number of coordinate systems - 2
	Coordinate system name - leftWingSkin
	Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 2
	Name = ritePointLoad, index = 1
	Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 4
	Name = upperWing, index = 1
	Name = lowerWing, index = 2
	Name = leftTip, index = 3
	Name = riteTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
	Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 265
	Number of elements = 346
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 346
Aero_Reference value is NULL - No aero reference parameters set

Getting FEA materials.......
	Number of materials - 2
	Material name - Madeupium
	Material name - Unobtainium
	No "materialType" specified for Material tuple Unobtainium, defaulting to "Isotropic"
	Done getting FEA materials

Getting FEA properties.......
	Number of properties - 5
	Property name - leftWingSkin
	Property name - riteWingSkin
	Property name - wingRib
	Property name - wingSpar1
	Property name - wingSpar2
	Done getting FEA properties
Updating mesh element types based on properties input

Getting FEA constraints.......
	Number of constraints - 1
	Constraint name - rootConstraint
	No "constraintType" specified for Constraint tuple rootConstraint, defaulting to "ZeroDisplacement"
	Done getting FEA constraints
Support tuple is NULL - No supports applied
Connect tuple is NULL - Using defaults

Getting FEA loads.......
	Number of loads - 1
	Load name - pressureAero
	No "groupName" specified for Load tuple pressureAero, going to use load name
	Done getting FEA loads
Optimization Control tuple is NULL - Default optimization control is used

Getting FEA optimization control.......
Done getting FEA Optimization Control
Design_Variable tuple is NULL - No design variables applied
Design_Constraint tuple is NULL - No design constraints applied
Analysis tuple is NULL

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Default
	Done getting FEA analyses
 CAPS Info: Reparameterization Bound -> upperWing -- nu, nv = 129 129
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 16
	Number of data points = 8945
 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.247769e+09, tgt = 6.247769e+09, diff = 5.859232e-01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 16
	Number of data points = 8945
 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.100462e+09, tgt = 6.100462e+09, diff = 5.488014e-02
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 16
	Number of data points = 8945
 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.121567e+07, tgt = 6.121567e+07, diff = 1.005828e-06
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 16
	Number of data points = 8945
 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.124703e+07, tgt = 6.124703e+07, diff = 1.490116e-08
Extracting external pressure loads from data transfer....
	TransferName = upperWing
	Number of Elements = 96 (total = 96)
Extracting external pressure loads from data transfer....
	TransferName = lowerWing
	Number of Elements = 96 (total = 192)
Extracting external pressure loads from data transfer....
	TransferName = leftTip
	Number of Elements = 10 (total = 202)
Extracting external pressure loads from data transfer....
	TransferName = riteTip
	Number of Elements = 10 (total = 212)

Writing Astros grid and connectivity file (in free field format) ....
Finished writing Astros grid file

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint cards--each subcase individually
	Writing load cards
	Writing material cards
	Writing property cards
	Writing coordinate system cards


Running mASTROS......

==> Running ASTROS post-analysis...

==> Running SU2 pre-analysis...
Writing boundary flags
 - bcProps.surfaceProp[0].surfaceType = 3
 - bcProps.surfaceProp[1].surfaceType = 1
Done boundary flags
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.5.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

----------------- Physical Case Definition ( Zone 0 ) -------------------
Input mesh file name: ../aflr3/aflr3_0.su2

---------------- Grid deformation parameters ( Zone 0 )  ----------------
Grid deformation using a linear elasticity method.


-------------------- Output Information ( Zone 0 ) ----------------------
Output mesh file name: ../aflr3/aflr3_0.su2. 
Cell stiffness scaled by distance to nearest solid surface.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_1|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_2|
+-----------------------------------------------------------------------+
Three dimensional problem.
81416 grid points.
454422 volume elements.
2 surface markers.
17886 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
454422 tetrahedra.

----------------------- Preprocessing computations ----------------------
Setting local point connectivity.
Checking the numerical grid orientation of the interior elements.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identify edges and vertices.
Setting the bound control volume structure.
Volume of the computational grid: 3.71806e+06.
  Info: Ignoring the following volume output fields/groups:
  SOLUTION
Volume output fields: COORDINATES
  Info: Ignoring the following screen output fields:
  RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME
  Info: Ignoring the following history output groups:
  RMS_RES, AERO_COEFF
History output group(s): ITER, TIME_DOMAIN, WALL_TIME
Warning: No (valid) fields chosen for convergence monitoring. Convergence monitoring inactive.
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.

--------------------- Surface grid deformation (ZONE 0) -----------------
Performing the deformation of the surface grid.
Updating the surface coordinates from the input file.

------------------- Volumetric grid deformation (ZONE 0) ----------------
Performing the deformation of the volumetric grid.

WARNING: Convexity is not checked for 3D elements (issue #1171).


Completed in 28.151973 seconds on 1 core.

----------------------- Write deformed grid files -----------------------
|SU2 mesh                           |../aflr3/aflr3_0.su2               |
|CSV file                           |surface_deformed.csv               |
|Tecplot binary                     |volume_deformed.szplt              |
|Tecplot binary surface             |surface_deformed.szplt             |
Adding any FFD information to the SU2 file.

------------------------- Finalize Solver -------------------------
Deleted CNumerics container.
Deleted CSolver container.
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

------------------------- Exit Success (SU2_DEF) ------------------------


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 8.0.0 "Harrier"                           |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2023, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
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| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.294118.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 10 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 7.74597 m.
Reference origin for moment evaluation is (0.322749, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.

Surface(s) plotted in the output file: BC_1.
Surface(s) affected by the design variables: BC_1.
Input mesh file name: ../aflr3/aflr3_0.su2

--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1. 
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.

--------------- Time Numerical Integration  ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
|  MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
|         0|         1|         0|         0|
|         1|         2|         0|         0|
|         2|         3|         0|         0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number:       10

------------------ Convergence Criteria  ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_aeroelasticIterative.dat.
Surface file name: surface_flow_aeroelasticIterative.
Volume file name: flow_aeroelasticIterative.
Restart file name: restart_flow_aeroelasticIterative.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_1|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_2|
+-----------------------------------------------------------------------+

-------------------- Output Preprocessing ( Zone 0 ) --------------------

WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)

Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
81416 grid points.
454422 volume elements.
2 surface markers.
17886 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
454422 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 206677 TETRAHEDRON volume elements.
There has been a re-orientation of 4617 TRIANGLE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 1.44958e+17.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 2.87656. Mean K: 0.00648455. Standard deviation K: 0.0464997.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|       0.137541|         84.713|
|     CV Face Area Aspect Ratio|        1.95221|    1.70288e+06|
|           CV Sub-Volume Ratio|              1|    4.01198e+09|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     81416|    1/1.00|        10|
|         1|     13381|    1/6.08|   8.21645|
|         2|      2059|     1/6.5|   6.60437|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 82958.1 m.
Wetted area = 2.72489e+11 m^2.
Area projection in the x-plane = 1.26495e+11 m^2, y-plane = 4.14598e+10 m^2, z-plane = 2.88447e+09 m^2.
Max. coordinate in the x-direction = 3741.21 m, y-direction = 82958.1 m, z-direction = 0.13057 m.
Min. coordinate in the x-direction = -24654.1 m, y-direction = -120901 m, z-direction = -1.49006e+06 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.

-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        211798|             1|   m^2/s^2|        211798|
|            Velocity-X|       100.087|             1|       m/s|       100.087|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|             0|             1|       m/s|             0|
|    Velocity Magnitude|       100.087|             1|       m/s|       100.087|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|      0.294118|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

------------------- Numerics Preprocessing ( Zone 0 ) -------------------

----------------- Integration Preprocessing ( Zone 0 ) ------------------

------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.

------------------------------ Begin Solver -----------------------------

Simulation Run using the Single-zone Driver
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
         see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  3.9611e+00|   11.162790|   14.130381|   14.018425|   16.631896|   -0.040154|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  4.2680e+00|   11.290199|   14.034216|   13.933524|   16.745064|   -0.034978|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  4.4743e+00|   11.451670|   14.100823|   13.982306|   16.865644|   -0.040030|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  4.5504e+00|   11.520505|   14.157753|   14.065040|   16.980595|   -0.032394|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  4.3620e+00|   11.581537|   14.205442|   14.102554|   17.047710|   -0.043549|

----------------------------- Solver Exit -------------------------------

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       11.5815|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticIterative.dat|

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|CSV file                           |surface_flow_aeroelasticIterative.csv|

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary                     |flow_aeroelasticIterative.szplt    |

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
|Tecplot binary surface             |surface_flow_aeroelasticIterative.szplt|

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).
+-----------------------------------------------------------------------+
Warning: there are 2467 non-physical points in the solution.
Warning: 730 reconstructed states for upwinding are non-physical.

--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------


==> Running SU2 post-analysis...

==> Running ASTROS pre-analysis...
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 16
	Number of data points = 8945
 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
            Rank 0: src = 3.818419e+09, tgt = 3.818419e+09, diff = 1.426175e+02
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 16
	Number of data points = 8945
 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
            Rank 0: src = 3.521819e+09, tgt = 3.521818e+09, diff = 7.450709e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 16
	Number of data points = 8945
 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
            Rank 0: src = 1.749554e+07, tgt = 1.749554e+07, diff = 0.000000e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 16
	Number of data points = 8945
 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
            Rank 0: src = 2.733346e+07, tgt = 2.733346e+07, diff = 0.000000e+00
Extracting external pressure loads from data transfer....
	TransferName = upperWing
	Number of Elements = 96 (total = 96)
Extracting external pressure loads from data transfer....
	TransferName = lowerWing
	Number of Elements = 96 (total = 192)
Extracting external pressure loads from data transfer....
	TransferName = leftTip
	Number of Elements = 10 (total = 202)
Extracting external pressure loads from data transfer....
	TransferName = riteTip
	Number of Elements = 10 (total = 212)

Writing Astros grid and connectivity file (in free field format) ....
Finished writing Astros grid file

Writing subElement types (if any) - appending mesh file

Writing Astros instruction file....
	Writing analysis cards
	Writing load ADD cards
	Writing constraint cards--each subcase individually
	Writing load cards
	Writing material cards
	Writing property cards
	Writing coordinate system cards


Running mASTROS......

==> Running ASTROS post-analysis...

real	2m32.991s
user	2m31.941s
sys	1m8.793s
+ status=0
+ set +x

=================================================
data/session11/aeroelastic_2_Iterative_SU2_Astros.py passed (as expected)
=================================================


*************************************************
*************************************************

=================================================
Did not run examples for:

session08 fun3d
session11 fun3d+astros
=================================================

All tests pass!

[Execution node] check if [reynolds] is in [[windows10x64]]
Run condition [Execution node ] preventing perform for step [Execute Windows batch command]
[GNU C Compiler (gcc)] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64')
[Clang] Skipping post processing
[Clang] No filter has been set, publishing all 0 issues
[Clang] Repository miner is not configured, skipping repository mining
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64')
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.6/CAPS/training/LINUX64')
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] No valid reference build found
[Static Analysis] All reported issues will be considered outstanding
[Static Analysis] No quality gates have been set - skipping
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_RegCaps/CASREV=7.6,ESPTEST=CAPS/training,ESP_ARCH=LINUX64,buildnode=reynolds #619'.
[Checks API] No suitable checks publisher found.
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] done
Finished: SUCCESS