Console Output

Skipping 2,340 KB.. Full Log
|         0|    144047|    1/1.00|        10|
|         1|     23626|     1/6.1|   8.21082|
|         2|      3582|     1/6.6|   6.56734|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 97.6729 m.
Wetted area = 8684.95 m^2.
Area projection in the x-plane = 678.501 m^2, y-plane = 443.209 m^2, z-plane = 4163.52 m^2.
Max. coordinate in the x-direction = 127.552 m, y-direction = 97.6729 m, z-direction = 7.71806 m.
Min. coordinate in the x-direction = 54 m, y-direction = -97.6729 m, z-direction = -5.479 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker 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|        221265|             1|   m^2/s^2|        221265|
|            Velocity-X|       170.123|             1|       m/s|       170.123|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|        2.9695|             1|       m/s|        2.9695|
|    Velocity Magnitude|       170.149|             1|       m/s|       170.149|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|           0.5|
+------------------------------------------------------------------------------+
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
+----------------------------------------------------------------+
|  Inner_Iter|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|
+----------------------------------------------------------------+
|           0|    0.940079|    3.216673|    2.937983|    6.422925|
|           1|    0.983382|    3.477963|    3.121180|    6.482902|
|           2|    1.061743|    3.604844|    3.405397|    6.550779|
|           3|    1.120205|    3.712026|    3.556017|    6.605438|
|           4|    1.169110|    3.786936|    3.637574|    6.660099|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       1.16911|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 restart                        |restart_flow_inviscidWing.dat      |
|CSV file                           |surface_flow_inviscidWing.csv      |
|Paraview                           |flow_inviscidWing.vtu              |
|Paraview surface                   |surface_flow_inviscidWing.vtu      |
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).

------------------------- Solver Postprocessing -------------------------
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) ------------------------


==> Total Forces and Moments
--> Cl =  0.321737 Cd =  0.008802
--> Cmx =  -5.6e-05 Cmy =  -0.052885 Cmz =  1.1e-05
--> Cx =  0.003185 Cy =  -2.1e-05 Cz =  0.321842

real	1m9.661s
user	0m59.919s
sys	0m4.271s
+ status=0
+ set +x

=================================================
data/session08/su2_1_InviscidWing.py passed (as expected)
=================================================


=================================================
tess_1_Geom.py test;
+ python tess_1_Geom.py
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)

real	0m40.215s
user	2m24.307s
sys	0m5.311s
+ status=0
+ set +x

=================================================
data/session09/tess_1_Geom.py  passed (as expected)
=================================================


=================================================
tess_2_TFI_Templates.py test;
+ python tess_2_TFI_Templates.py
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 11079
Number of elements = 22781
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 22781
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 11079
Total number of elements = 22781
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 11911
Number of elements = 24445
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 24445
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 11911
Total number of elements = 24445

real	0m43.314s
user	2m33.151s
sys	0m5.997s
+ status=0
+ set +x

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


=================================================
tess_3_Params.py test;
+ python tess_3_Params.py
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 728
Number of elements = 1771
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 1771
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 728
Total number of elements = 1771
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 929
Number of elements = 2217
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 2217
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 929
Total number of elements = 2217
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 3548
Number of elements = 7675
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 7675
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3548
Total number of elements = 7675

real	0m41.571s
user	2m29.424s
sys	0m5.000s
+ 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 /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 1412
Number of elements = 3153
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 3153
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 1412
Total number of elements = 3153
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 2096
Number of elements = 4571
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 4571
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 2096
Total number of elements = 4571
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 6555
Number of elements = 13674
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 13674
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 6555
Total number of elements = 13674

real	0m47.323s
user	2m37.416s
sys	0m4.774s
+ 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 /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 3562
Number of elements = 7467
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 7467
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3562
Total number of elements = 7467
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 12400
Number of elements = 25271
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 25271
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 12400
Total number of elements = 25271
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 44953
Number of elements = 90575
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 90575
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 44953
Total number of elements = 90575

real	0m51.841s
user	2m45.514s
sys	0m5.092s
+ 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 /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 8299
Number of elements = 17185
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17185
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 8299
Total number of elements = 17185
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
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_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
Number of nodes    = 8299
Number of elements = 17185
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17185
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 8299
Total number of elements = 17185
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
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

real	1m17.728s
user	3m6.227s
sys	0m5.460s
+ 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 /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
Number of nodes    = 8299
Number of elements = 17185
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17185
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 8299
Total number of elements = 17185
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, 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)
	Tessellating body
Number of nodes    = 3890
Number of elements = 8352
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 8352
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3890
Total number of elements = 8352
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, 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)
	Tessellating body
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	0m44.326s
user	2m35.100s
sys	0m5.209s
+ 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 /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
Number of nodes    = 8299
Number of elements = 17185
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17185
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 8299
Total number of elements = 17185
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4

Getting mesh sizing parameters
	Mesh sizing name - leadingEdge
	Mesh sizing name - rootLeadingEdge
	Mesh sizing name - wingSpar1
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
Number of nodes    = 12931
Number of elements = 27404
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 27404
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 12931
Total number of elements = 27404
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4

Getting mesh sizing parameters
	Mesh sizing name - leadingEdge
	Mesh sizing name - rootLeadingEdge
	Mesh sizing name - wingSpar1
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
Number of nodes    = 9547
Number of elements = 10090
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 10090
----------------------------
Total number of nodes    = 9547
Total number of elements = 10090

real	0m44.469s
user	2m41.045s
sys	0m5.522s
+ status=0
+ set +x

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


=================================================
tess_MinQuad.py test;
+ python tess_MinQuad.py
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../../data/ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
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	0m34.581s
user	2m23.876s
sys	0m5.154s
+ status=0
+ set +x

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


=================================================
tess_2k.py test;
+ python tess_2k.py
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../../data/ESP/wing3.csm"...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, 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)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
Number of nodes    = 1605
Number of elements = 1823
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 1823
----------------------------
Total number of nodes    = 1605
Total number of elements = 1823
--> Total Elements 1823

real	0m38.609s
user	2m24.961s
sys	0m5.333s
+ status=0
+ set +x

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


=================================================
astros_1_ModalClamped.py test;
+ python astros_1_ModalClamped.py
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
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
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 = riteTip, index = 3
	Name = leftTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
capsIgnore attribute found. Removing unneeded nodes and elements from mesh!
Removing unused nodes...
	Removed 64 (out of 299) unused nodes!
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

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

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 : 0.0357647
    3 : 0.102451
    4 : 0.102451
    5 : 0.159637
    6 : 0.159637
    7 : 0.215446
    8 : 0.215446
    9 : 0.350115
    10: 0.350115

real	0m41.539s
user	2m26.375s
sys	0m5.723s
+ status=0
+ set +x

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


=================================================
astros_2_ModalSupport.py test;
+ python astros_2_ModalSupport.py
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = ribSupport, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 2)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
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
Getting surface mesh for body 2 (of 2)
	Tessellating body
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    = 300
Total number of elements = 388
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 = riteTip, index = 3
	Name = leftTip, 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 capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
	Name = ribSupport, index = 6
capsIgnore attribute found. Removing unneeded nodes and elements from mesh!
Removing unused nodes...
	Removed 64 (out of 299) unused nodes!
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

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 300)
	Done getting FEA connections
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

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 : 0.0533161
    3 : 0.102451
    4 : 0.102496
    5 : 0.159637
    6 : 0.211734
    7 : 0.215446
    8 : 0.223928
    9 : 0.350115
    10: 0.432754

real	0m39.666s
user	2m25.388s
sys	0m5.425s
+ 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 /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
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
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 = riteTip, index = 3
	Name = leftTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
capsIgnore attribute found. Removing unneeded nodes and elements from mesh!
Removing unused nodes...
	Removed 64 (out of 299) unused nodes!
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

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
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 43461.879146949635
--> T1max 738.594
--> T2max 3686.25
--> T3max 43363.8

real	0m39.688s
user	2m25.735s
sys	0m5.210s
+ 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 /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
	capsIgnore attribute found for face - 6!!
	capsIgnore attribute found for face - 11!!
	capsIgnore attribute found for face - 12!!
	capsIgnore attribute found for face - 13!!
	capsIgnore attribute found for face - 22!!
	capsIgnore attribute found for face - 24!!
	capsIgnore attribute found for face - 25!!
	capsIgnore attribute found for face - 32!!
	capsIgnore attribute found for face - 33!!
	capsIgnore attribute found for face - 34!!
	capsIgnore attribute found for face - 36!!
	capsIgnore attribute found for face - 37!!
	capsIgnore attribute found for face - 38!!
	capsIgnore attribute found for face - 39!!
	capsIgnore attribute found for face - 46!!
	capsIgnore attribute found for face - 48!!
	capsIgnore attribute found for face - 49!!
	capsIgnore attribute found for face - 50!!
	capsIgnore attribute found for face - 51!!
	capsIgnore attribute found for face - 58!!
	capsIgnore attribute found for face - 59!!
	capsIgnore attribute found for face - 61!!
	capsIgnore attribute found for face - 62!!
	capsIgnore attribute found for face - 63!!
	capsIgnore attribute found for face - 70!!
	capsIgnore attribute found for face - 72!!
	capsIgnore attribute found for face - 73!!
	capsIgnore attribute found for face - 74!!
	capsIgnore attribute found for face - 75!!
	capsIgnore attribute found for face - 81!!
	capsIgnore attribute found for face - 82!!
	capsIgnore attribute found for face - 84!!
	capsIgnore attribute found for face - 85!!
	capsIgnore attribute found for face - 86!!
	capsIgnore attribute found for face - 92!!
	capsIgnore attribute found for face - 93!!
	capsIgnore attribute found for face - 94!!
	capsIgnore attribute found for face - 96!!
	capsIgnore attribute found for face - 97!!
	capsIgnore attribute found for face - 98!!
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
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 = riteTip, index = 3
	Name = leftTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
capsIgnore attribute found. Removing unneeded nodes and elements from mesh!
Removing unused nodes...
	Removed 64 (out of 299) unused nodes!
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

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
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	0m39.441s
user	2m24.259s
sys	0m5.629s
+ 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 /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...

==> Running Nastran pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000206 at [[/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/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 = 7
	Name = Wing, index = 1
	Name = wingSpar1, index = 2
	Name = wingRib, index = 3
	Name = riteWingSkin, index = 4
	Name = leftWingSkin, index = 5
	Name = wingSpar2, index = 6
	Name = wingTE, index = 7
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 4)
	Tessellating body
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
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Number of nodes    = 7
Number of elements = 3
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 3
Getting surface mesh for body 2 (of 4)
	Tessellating body
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
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Number of nodes    = 7
Number of elements = 3
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 3
Getting surface mesh for body 3 (of 4)
	Tessellating body
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
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Number of nodes    = 7
Number of elements = 3
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 3
Getting surface mesh for body 4 (of 4)
	Tessellating body
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    = 320
Total number of elements = 396
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 = riteTip, index = 3
	Name = leftTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 7
	Name = Wing, index = 1
	Name = wingSpar1, index = 2
	Name = wingRib, index = 3
	Name = riteWingSkin, index = 4
	Name = leftWingSkin, index = 5
	Name = wingSpar2, index = 6
	Name = wingTE, index = 7
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 7
	Number of elements = 3
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 3
Setting FEA Data
	Mesh for body = 1
	Number of nodal coordinates = 7
	Number of elements = 3
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 3
Setting FEA Data
	Mesh for body = 2
	Number of nodal coordinates = 7
	Number of elements = 3
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 3
Setting FEA Data
	Mesh for body = 3
	Number of nodal coordinates = 299
	Number of elements = 387
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 387
Combining multiple FEA meshes!
	Combined Number of nodal coordinates = 320
	Combined Number of elements = 396
	Combined Elemental Nodes = 0
	Combined Elemental Rods  = 0
	Combined Elemental Tria3 = 0
	Combined Elemental Quad4 = 396
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 = 12
	Surface 2: Number of points found for aero-spline = 12

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: nastran: command not found

real	0m42.251s
user	2m29.158s
sys	0m5.290s
+ 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 /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/training.log

==> 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 9.13.17
AFLR2    : Version Date   02/08/21 @ 01:41PM
AFLR2    : Compile OS     Darwin 19.6.0 x86_64
AFLR2    : Compile Date   08/28/21 @ 12:27AM
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 10.17.5
AFLR4    : Version Date   08/28/21 @ 12:04AM
AFLR4    : Compile OS     Darwin 19.6.0 x86_64
AFLR4    : Compile Date   08/28/21 @ 12:24PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Desi@n System
EGADS    : Version 1.21
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

EGADS    : EGADS CAD Geometry Setup

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

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    : 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, Faces      =      1658      3135
AFLR4    : Nodes, Faces      =       983      1785

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Faces      =      1628      3077
AFLR4    : Nodes, Faces      =       934      1689

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

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Faces      =      1668      3155
AFLR4    : Nodes, Faces      =       974      1767

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Faces      =      1625      3071
AFLR4    : Nodes, Faces      =       918      1657

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

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

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

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

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

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

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

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      3828      7648       938

AFLR4    : Curvature BG Surface Grid Generation

AFLR4    : Nodes, Faces      =      3828      7648

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Faces      =      3391      6471
AFLR4    : Nodes, Faces      =      2424      4537

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Faces      =      3389      6468
AFLR4    : Nodes, Faces      =      2255      4200

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Faces      =       145       226
AFLR4    : Nodes, Faces      =       137       210

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Faces      =      3360      6409
AFLR4    : Nodes, Faces      =      2432      4553

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Faces      =      3367      6424
AFLR4    : Nodes, Faces      =      2298      4286

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Faces      =       145       226
AFLR4    : Nodes, Faces      =       137       210

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

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

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

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

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

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

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      9320     18632      1526

OVERALL  : CPU Time          =     0.492   seconds

EGADS    : CREATE EGADS TESS FROM AFLR4 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

Body = 1
Number of nodes = 9000
Number of elements = 17996
Number of tris = 17996
Number of quad = 0
Body = 2
Number of nodes = 320
Number of elements = 636
Number of tris = 636
Number of quad = 0
----------------------------
Total number of nodes = 9320
Total number of elements = 18632
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
Number of surface nodes - 9320
Number of surface elements - 18632
Getting volume mesh
 
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
 
UG PARAM : mrecm                       = 3         
UG PARAM : mrecqm                      = 3         
 
AFLR3    : ---------------------------------------
AFLR3    : AFLR3 LIBRARY
AFLR3    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR3    : TETRAHEDRAL GRID GENERATOR
AFLR3    : Version Number 16.31.6
AFLR3    : Version Date   08/30/21 @ 12:37AM
AFLR3    : Compile OS     Darwin 19.6.0 x86_64
AFLR3    : Compile Date   08/30/21 @ 12:37AM
AFLR3    : Copyright 1994-2021, D.L. Marcum
AFLR3    : ---------------------------------------
 
AFLR3 IC : INPUT SURFACE GRID CHECK
 
AFLR3 IC : Nodes, Elements   =      9320         0

UG3      : Boundary Conditions

UG3      :  B-Face ID            Boundary Condition
UG3      :          1                      FarField
UG3      :          2                      FarField
 
AFLR3    : CPU Time          =     0.032   seconds
 
AFLR3 IG : INITIAL VOLUME GRID GENERATION
 
AFLR3 IG : Nodes, Elements   =      9320         0
AFLR3 IG : Nodes, Elements   =         8        10
AFLR3 IG : Nodes, Elements   =      1866     12839
AFLR3 IG : Nodes, Elements   =      3732     26197
AFLR3 IG : Nodes, Elements   =      5598     39670
AFLR3 IG : Nodes, Elements   =      7464     54240
AFLR3 IG : Nodes, Elements   =      9327     69967
AFLR3 IG : Nodes, Elements   =      9327     69775
AFLR3 IG : Nodes, Elements   =      9320     42615
AFLR3 IG : Nodes, Elements   =      9320     42684
AFLR3 IG : Nodes, Elements   =      9320     30692
AFLR3 IG : Nodes, Elements   =      9320     28365
 
AFLR3    : CPU Time          =     0.243   seconds
 
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
 
AFLR3 GG : Nodes, Elements   =      9320     28365
AFLR3 GG : Nodes, Elements   =     13635     41359
AFLR3 GG : Nodes, Elements   =     13635     59108
AFLR3 GG : Nodes, Elements   =     13635     54401
AFLR3 GG : Nodes, Elements   =     17287     65796
AFLR3 GG : Nodes, Elements   =     17287     79558
AFLR3 GG : Nodes, Elements   =     17287     74996
AFLR3 GG : Nodes, Elements   =     20811     85947
AFLR3 GG : Nodes, Elements   =     20811     99984
AFLR3 GG : Nodes, Elements   =     20811     95883
AFLR3 GG : Nodes, Elements   =     24442    106895
AFLR3 GG : Nodes, Elements   =     24442    121233
AFLR3 GG : Nodes, Elements   =     24442    117198
AFLR3 GG : Nodes, Elements   =     28202    128566
AFLR3 GG : Nodes, Elements   =     28202    143384
AFLR3 GG : Nodes, Elements   =     28202    139481
AFLR3 GG : Nodes, Elements   =     31926    150707
AFLR3 GG : Nodes, Elements   =     31926    165340
AFLR3 GG : Nodes, Elements   =     31926    161626
AFLR3 GG : Nodes, Elements   =     35553    172548
AFLR3 GG : Nodes, Elements   =     35553    186694
AFLR3 GG : Nodes, Elements   =     35553    183011
AFLR3 GG : Nodes, Elements   =     39080    193627
AFLR3 GG : Nodes, Elements   =     39080    207451
AFLR3 GG : Nodes, Elements   =     39080    203946
AFLR3 GG : Nodes, Elements   =     42509    214277
AFLR3 GG : Nodes, Elements   =     42509    227541
AFLR3 GG : Nodes, Elements   =     42509    224214
AFLR3 GG : Nodes, Elements   =     45756    233982
AFLR3 GG : Nodes, Elements   =     45756    246838
AFLR3 GG : Nodes, Elements   =     45756    243617
AFLR3 GG : Nodes, Elements   =     48925    253149
AFLR3 GG : Nodes, Elements   =     48925    265460
AFLR3 GG : Nodes, Elements   =     48925    262346
AFLR3 GG : Nodes, Elements   =     51945    271413
AFLR3 GG : Nodes, Elements   =     51945    283380
AFLR3 GG : Nodes, Elements   =     51945    280286
AFLR3 GG : Nodes, Elements   =     54837    288985
AFLR3 GG : Nodes, Elements   =     54837    300386
AFLR3 GG : Nodes, Elements   =     54837    297550
AFLR3 GG : Nodes, Elements   =     57608    305877
AFLR3 GG : Nodes, Elements   =     57608    316834
AFLR3 GG : Nodes, Elements   =     57608    314009
AFLR3 GG : Nodes, Elements   =     60213    321834
AFLR3 GG : Nodes, Elements   =     60213    331996
AFLR3 GG : Nodes, Elements   =     60213    329490
AFLR3 GG : Nodes, Elements   =     62667    336860
AFLR3 GG : Nodes, Elements   =     62667    346428
AFLR3 GG : Nodes, Elements   =     62667    344140
AFLR3 GG : Nodes, Elements   =     64969    351048
AFLR3 GG : Nodes, Elements   =     64969    359993
AFLR3 GG : Nodes, Elements   =     64969    357798
AFLR3 GG : Nodes, Elements   =     67143    364328
AFLR3 GG : Nodes, Elements   =     67143    372867
AFLR3 GG : Nodes, Elements   =     67143    370745
AFLR3 GG : Nodes, Elements   =     69130    376714
AFLR3 GG : Nodes, Elements   =     69130    384467
AFLR3 GG : Nodes, Elements   =     69130    382542
AFLR3 GG : Nodes, Elements   =     71044    388292
AFLR3 GG : Nodes, Elements   =     71044    395832
AFLR3 GG : Nodes, Elements   =     71044    393993
AFLR3 GG : Nodes, Elements   =     72805    399277
AFLR3 GG : Nodes, Elements   =     72805    406216
AFLR3 GG : Nodes, Elements   =     72805    404507
AFLR3 GG : Nodes, Elements   =     74459    409474
AFLR3 GG : Nodes, Elements   =     74459    415879
AFLR3 GG : Nodes, Elements   =     74459    414304
AFLR3 GG : Nodes, Elements   =     75979    418869
AFLR3 GG : Nodes, Elements   =     75979    424867
AFLR3 GG : Nodes, Elements   =     75979    423367
AFLR3 GG : Nodes, Elements   =     77380    427572
AFLR3 GG : Nodes, Elements   =     77380    433057
AFLR3 GG : Nodes, Elements   =     77380    431721
AFLR3 GG : Nodes, Elements   =     78690    435652
AFLR3 GG : Nodes, Elements   =     78690    440752
AFLR3 GG : Nodes, Elements   =     78690    439522
AFLR3 GG : Nodes, Elements   =     79929    443239
AFLR3 GG : Nodes, Elements   =     79929    448047
AFLR3 GG : Nodes, Elements   =     79929    446890
AFLR3 GG : Nodes, Elements   =     81027    450187
AFLR3 GG : Nodes, Elements   =     81027    454548
AFLR3 GG : Nodes, Elements   =     81027    453476
AFLR3 GG : Nodes, Elements   =     82024    456470
AFLR3 GG : Nodes, Elements   =     82024    460364
AFLR3 GG : Nodes, Elements   =     82024    459383
AFLR3 GG : Nodes, Elements   =     82879    461950
AFLR3 GG : Nodes, Elements   =     82879    465375
AFLR3 GG : Nodes, Elements   =     82879    464497
AFLR3 GG : Nodes, Elements   =     83509    466388
AFLR3 GG : Nodes, Elements   =     83509    468966
AFLR3 GG : Nodes, Elements   =     83509    468245
AFLR3 GG : Nodes, Elements   =     83950    469569
AFLR3 GG : Nodes, Elements   =     83950    471393
AFLR3 GG : Nodes, Elements   =     83950    470864
AFLR3 GG : Nodes, Elements   =     84204    471626
AFLR3 GG : Nodes, Elements   =     84204    472690
AFLR3 GG : Nodes, Elements   =     84204    472389
AFLR3 GG : Nodes, Elements   =     84362    472863
AFLR3 GG : Nodes, Elements   =     84362    473462
AFLR3 GG : Nodes, Elements   =     84362    473295
AFLR3 GG : Nodes, Elements   =     84430    473499
AFLR3 GG : Nodes, Elements   =     84430    473801
AFLR3 GG : Nodes, Elements   =     84430    473698
AFLR3 GG : Nodes, Elements   =     84465    473803
AFLR3 GG : Nodes, Elements   =     84465    473943
AFLR3 GG : Nodes, Elements   =     84465    473888
AFLR3 GG : Nodes, Elements   =     84476    473921
AFLR3 GG : Nodes, Elements   =     84476    473969
AFLR3 GG : Nodes, Elements   =     84476    473949
AFLR3 GG : Nodes, Elements   =     84478    473955
AFLR3 GG : Nodes, Elements   =     84478    473965
AFLR3 GG : Nodes, Elements   =     84478    473959
AFLR3 GG : Nodes, Elements   =     84485    473980
AFLR3 GG : Nodes, Elements   =     84485    474008
AFLR3 GG : Nodes, Elements   =     84485    473999
AFLR3 GG : Nodes, Elements   =     84487    474005
AFLR3 GG : Nodes, Elements   =     84487    474012
AFLR3 GG : Nodes, Elements   =     84487    474008
 
AFLR3    : CPU Time          =     3.503   seconds
 
AFLR3 QI : QUALITY IMPROVEMENT
 
AFLR3 QI : Nodes, Elements   =     84487    474008
AFLR3 QI : Nodes, Elements   =     84026    471404
AFLR3 QI : Nodes, Elements   =     83954    470992
AFLR3 QI : Nodes, Elements   =     83945    470939
AFLR3 QI : Nodes, Elements   =     83944    470933
AFLR3 QI : Nodes, Elements   =     83944    472869
AFLR3 QI : Nodes, Elements   =     83944    470664
AFLR3 QI : Nodes, Elements   =     83944    469683
AFLR3 QI : Nodes, Elements   =     83944    469902
AFLR3 QI : Nodes, Elements   =     83944    469495
AFLR3 QI : Nodes, Elements   =     83944    469396
 
AFLR3    : CPU Time          =     0.891   seconds
 
AFLR3    : DONE

UG3      : DIHEDRAL ANGLE CHECK

UG3      : No. Tet Elems     =    469396
UG3      : Min, Max Ang      =     13.81     152.5
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     =    469396
UG3      : Min Vol           =  1.01e-06
UG3      : Average Vol       =      7.92
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     =    469396
UG3      : Min, Max Q        =     0.271         1
UG3      : Average Q         =     0.897
UG3      : No. Q<       0.1  =         0
UG3      : No. Q<      0.01  =         0
 
UG_IO    : OUTPUT GRID
 
UG_IO    : Writing Data
 
UG_IO    : Grid File Name    = /Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64/CAPS/training/data/session11/workDir_2_Aeroelastic_Iterative/Scratch/aflr3/aflr3.lb8.ugrid
UG_IO    : Quad Surface Faces=         0
UG_IO    : Tria Surface Faces=     18632
UG_IO    : Quad Int. Faces   =         0
UG_IO    : Tria Int. Faces   =    929476
UG_IO    : Nodes             =     83944
UG_IO    : Total Elements    =    469396
UG_IO    : Hex Elements      =         0
UG_IO    : Pent_5 Elements   =         0
UG_IO    : Pent_6 Elements   =         0
UG_IO    : Tet Elements      =    469396
 
UG_IO    : CPU Time          =     0.049   seconds
Volume mesh:
	Number of nodes = 83944
	Number of elements = 488028
	Number of triangles = 18632
	Number of quadrilatarals = 0
	Number of tetrahedrals = 469396
	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

Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Wing, index = 1
	Name = Farfield, index = 2
Getting CFD boundary conditions
	Boundary condition name - Farfield
	Boundary condition name - Wing
	Done getting CFD boundary conditions
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 (7.2.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.2.0 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   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 2012-2021, 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: 1.

Surface(s) plotted in the output file: 1.
Surface(s) affected by the design variables: 1.
Input mesh file name: ../aflr3/aflr3.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 ) ----------------------
Writing solution files every 250 iterations.
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|                                  1|
+-----------------------------------------------------------------------+
|                          Far-field|                                  2|
+-----------------------------------------------------------------------+

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

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

Screen output fields: INNER_ITER, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY
History output group(s): ITER, RMS_RES
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.
83944 grid points.
469396 volume elements.
2 surface markers.
17996 boundary elements in index 0 (Marker = 1).
636 boundary elements in index 1 (Marker = 2).
469396 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: 20.5054. Standard deviation K: 49.1968.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        46.4554|        86.5344|
|     CV Face Area Aspect Ratio|        1.05258|        102.843|
|           CV Sub-Volume Ratio|              1|        681.984|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     83944|    1/1.00|        10|
|         1|     13872|    1/6.05|   8.23141|
|         2|      2140|    1/6.48|   6.62202|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5565 m^2.
Area projection in the x-plane = 1.53007 m^2, y-plane = 0.868422 m^2, z-plane = 9.83485 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 = -0.0329185 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker 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
+----------------------------------------------------------------+
|  Inner_Iter|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|
+----------------------------------------------------------------+
|           0|   -1.772063|    0.446920|    0.049177|    3.697043|
|           1|   -1.601203|    0.812503|    0.478627|    3.876373|
|           2|   -1.616686|    0.937288|    0.737875|    3.859321|
|           3|   -1.742129|    0.927787|    0.786181|    3.719978|
|           4|   -1.642753|    0.826369|    0.695244|    3.820459|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.64275|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 restart                        |restart_flow_aeroelasticIterative.dat|
|CSV file                           |surface_flow_aeroelasticIterative.csv|
|Tecplot binary                     |flow_aeroelasticIterative.szplt    |
|Tecplot binary surface             |surface_flow_aeroelasticIterative.szplt|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).

------------------------- Solver Postprocessing -------------------------
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 = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar1, index = 1
	Name = wingSpar2, index = 2
	Name = rootLeadingEdge, index = 3
	Name = leadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
	Tessellating body
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 = riteTip, index = 3
	Name = leftTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar1, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = leftWingSkin, index = 4
	Name = wingSpar2, 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
 CAPS Info: Reparameterization Bound -> upperWing -- nu, nv = 129 129
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.247781e+09, tgt = 6.247781e+09, diff = 2.732474e+00
 CAPS Info: Reparameterization Bound -> lowerWing -- nu, nv = 129 129
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.099734e+09, tgt = 6.099734e+09, diff = 2.791156e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.123597e+07, tgt = 6.123597e+07, diff = 0.000000e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.120998e+07, tgt = 6.120998e+07, diff = 0.000000e+00

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
Extracting external pressure loads from data transfer....
	TransferName = upperWing
	Number of Elements = 96 (total = 96)
	TransferName = lowerWing
	Number of Elements = 96 (total = 192)
	TransferName = leftTip
	Number of Elements = 10 (total = 202)
	TransferName = riteTip
	Number of Elements = 10 (total = 212)
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......

==> Running ASTROS post-analysis...

==> Running SU2 pre-analysis...
Getting CFD boundary conditions
	Boundary condition name - Farfield
	Boundary condition name - Wing
	Done getting CFD boundary conditions
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 (7.2.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.2.0 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Mesh Deformation Code)                     |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2021, 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.su2

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


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

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                                  1|
+-----------------------------------------------------------------------+
|                          Far-field|                                  2|
+-----------------------------------------------------------------------+
Three dimensional problem.
83944 grid points.
469396 volume elements.
2 surface markers.
17996 boundary elements in index 0 (Marker = 1).
636 boundary elements in index 1 (Marker = 2).
469396 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
Screen output fields: 
  Info: Ignoring the following history output groups:
  RMS_RES
History output group(s): ITER
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).


----------------------- Write deformed grid files -----------------------
|SU2 mesh                           |aeroelasticIterative.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.

------------------------- Solver Postprocessing -------------------------
Deleted CGeometry container.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted COutput class.

Completed in 28.244944 seconds on 1 core.

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


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.2.0 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   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 2012-2021, 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: 1.

Surface(s) plotted in the output file: 1.
Surface(s) affected by the design variables: 1.
Input mesh file name: ../aflr3/aflr3.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 ) ----------------------
Writing solution files every 250 iterations.
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|                                  1|
+-----------------------------------------------------------------------+
|                          Far-field|                                  2|
+-----------------------------------------------------------------------+

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

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

Screen output fields: INNER_ITER, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY
History output group(s): ITER, RMS_RES
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.
83944 grid points.
469396 volume elements.
2 surface markers.
17996 boundary elements in index 0 (Marker = 1).
636 boundary elements in index 1 (Marker = 2).
469396 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: 20.5054. Standard deviation K: 49.1968.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        46.4554|        86.5344|
|     CV Face Area Aspect Ratio|        1.05258|        102.843|
|           CV Sub-Volume Ratio|              1|        681.984|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     83944|    1/1.00|        10|
|         1|     13872|    1/6.05|   8.23141|
|         2|      2140|    1/6.48|   6.62202|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5565 m^2.
Area projection in the x-plane = 1.53007 m^2, y-plane = 0.868422 m^2, z-plane = 9.83485 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 = -0.0329185 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker 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
+----------------------------------------------------------------+
|  Inner_Iter|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|
+----------------------------------------------------------------+
|           0|   -1.772063|    0.446920|    0.049177|    3.697043|
|           1|   -1.601203|    0.812503|    0.478627|    3.876373|
|           2|   -1.616686|    0.937288|    0.737875|    3.859321|
|           3|   -1.742129|    0.927787|    0.786181|    3.719978|
|           4|   -1.642753|    0.826369|    0.695244|    3.820459|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.64275|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 restart                        |restart_flow_aeroelasticIterative.dat|
|CSV file                           |surface_flow_aeroelasticIterative.csv|
|Tecplot binary                     |flow_aeroelasticIterative.szplt    |
|Tecplot binary surface             |surface_flow_aeroelasticIterative.szplt|
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_aeroelasticIterative.dat).

------------------------- Solver Postprocessing -------------------------
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 = 13
	Number of data points = 9000
 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.247781e+09, tgt = 6.247781e+09, diff = 2.732474e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.099734e+09, tgt = 6.099734e+09, diff = 2.791156e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.123597e+07, tgt = 6.123597e+07, diff = 0.000000e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.120998e+07, tgt = 6.120998e+07, diff = 0.000000e+00

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
Extracting external pressure loads from data transfer....
	TransferName = upperWing
	Number of Elements = 96 (total = 96)
	TransferName = lowerWing
	Number of Elements = 96 (total = 192)
	TransferName = leftTip
	Number of Elements = 10 (total = 202)
	TransferName = riteTip
	Number of Elements = 10 (total = 212)
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......

==> Running ASTROS post-analysis...

real	3m41.087s
user	5m15.149s
sys	0m11.559s
+ status=0
+ set +x

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


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

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

session08 fun3d
session11 fun3d
=================================================

All tests pass!


=================================================
=================================================
[GNU C Compiler (gcc)] Sleeping for 5 seconds due to JENKINS-32191...
[GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64')
[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] Sleeping for 5 seconds due to JENKINS-32191...
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.6/CAPS/training/DARWIN64')
[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] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.6,CAPS/training,DARWIN64,macys)
[Static Analysis] No valid reference build found that meets the criteria (NO_JOB_FAILURE - SUCCESSFUL_QUALITY_GATE)
[Static Analysis] All reported issues will be considered outstanding
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality QualityGate: 1
[Static Analysis] -> All quality gates have been passed
[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_UndefinedCaps/CASREV=7.6,ESPTEST=CAPS/training,ESP_ARCH=DARWIN64,buildnode=macys #153'.
[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