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Skipping 2,350 KB.. Full Log
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 25.1444. Mean K: 1.31911. Standard deviation K: 3.07302.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        52.8789|        87.0788|
|     CV Face Area Aspect Ratio|        1.02024|        134.818|
|           CV Sub-Volume Ratio|        1.04253|           1008|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|    146357|    1/1.00|        10|
|         1|     24022|    1/6.09|   8.21277|
|         2|      3692|    1/6.51|    6.5988|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 97.6729 m.
Wetted area = 8686.36 m^2.
Area projection in the x-plane = 678.35 m^2, y-plane = 443.236 m^2, z-plane = 4164.26 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 = -5.47911 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.

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

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        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
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  5.8129e+00|    0.938580|    3.215149|    2.934655|    6.421425|   -0.381631|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  5.7320e+00|    1.004374|    3.477362|    3.113650|    6.501703|    0.082195|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  5.7142e+00|    1.107363|    3.624764|    3.405407|    6.593819|    1.629831|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  5.6425e+00|    1.179786|    3.742454|    3.581233|    6.658379|    7.056295|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  5.5980e+00|    1.257220|    3.830490|    3.677659|    6.742493|   38.919402|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       1.25722|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_inviscidWing.dat      |

Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
|CSV file                           |surface_flow_inviscidWing.csv      |

Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
|Paraview                           |flow_inviscidWing.vtu              |

Writing the forces breakdown file (forces_breakdown_inviscidWing.dat).
|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 =  0.321007 Cd =  0.008248
--> Cmx =  -0.000149 Cmy =  -0.052642 Cmz =  8.2e-05
--> Cx =  0.002644 Cy =  0.000155 Cz =  0.321102

real	1m4.674s
user	1m2.688s
sys	0m2.243s
+ 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 /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)

real	0m27.178s
user	1m14.986s
sys	2m45.422s
+ 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 /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 11058
Number of elements = 22735
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 22735
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 11058
Total number of elements = 22735
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 11915
Number of elements = 24449
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 24449
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 11915
Total number of elements = 24449

real	0m25.629s
user	1m27.373s
sys	2m43.571s
+ status=0
+ set +x

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


=================================================
tess_3_Params.py test;
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
+ python tess_3_Params.py

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 731
Number of elements = 1779
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 1779
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 731
Total number of elements = 1779
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 940
Number of elements = 2240
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 2240
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 940
Total number of elements = 2240
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 3543
Number of elements = 7661
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 7661
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3543
Total number of elements = 7661

real	0m21.197s
user	1m7.026s
sys	1m13.282s
+ status=0
+ set +x

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


=================================================
tess_4_Params.py test;
+ python tess_4_Params.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 1399
Number of elements = 3122
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 3122
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 1399
Total number of elements = 3122
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 2096
Number of elements = 4573
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 4573
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 2096
Total number of elements = 4573
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 6575
Number of elements = 13719
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 13719
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 6575
Total number of elements = 13719

real	0m23.593s
user	1m19.422s
sys	2m46.529s
+ status=0
+ set +x

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


=================================================
tess_5_Params.py test;
+ python tess_5_Params.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 3548
Number of elements = 7437
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 7437
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3548
Total number of elements = 7437
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 12429
Number of elements = 25326
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 25326
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 12429
Total number of elements = 25326
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 45308
Number of elements = 91283
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 91283
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 45308
Total number of elements = 91283

real	0m28.339s
user	1m28.863s
sys	2m34.435s
+ status=0
+ set +x

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


=================================================
tess_6_TriQuad.py test;
+ python tess_6_TriQuad.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 8266
Number of elements = 17115
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17115
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 8266
Total number of elements = 17115
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 72029
Number of elements = 74322
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 74322
----------------------------
Total number of nodes    = 72029
Total number of elements = 74322
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 1566
Number of elements = 3043
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 3043
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 1566
Total number of elements = 3043
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 3009
Number of elements = 2928
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 2928
----------------------------
Total number of nodes    = 3009
Total number of elements = 2928

real	0m41.459s
user	1m38.726s
sys	2m45.168s
+ status=0
+ set +x

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


=================================================
tess_7_MeshSizing.py test;
+ python tess_7_MeshSizing.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 8266
Number of elements = 17115
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17115
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 8266
Total number of elements = 17115
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4

Getting mesh sizing parameters
	Mesh sizing name - leadingEdge
	Mesh sizing name - rootLeadingEdge
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 3860
Number of elements = 8288
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 8288
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3860
Total number of elements = 8288
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4

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

real	0m37.719s
user	1m36.222s
sys	2m44.789s
+ status=0
+ set +x

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


=================================================
tess_8_MeshSizing.py test;
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
+ python tess_8_MeshSizing.py

==> Loading geometry from file "../ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 1566
Number of elements = 3043
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 3043
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 1566
Total number of elements = 3043
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3

Getting mesh sizing parameters
	Mesh sizing name - rootLeadingEdge
	Mesh sizing name - wingSpar1
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 6582
Number of elements = 13186
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 13186
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 6582
Total number of elements = 13186
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3

Getting mesh sizing parameters
	Mesh sizing name - rootLeadingEdge
	Mesh sizing name - wingSpar1
	Done getting mesh sizing parameters
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 22194
Number of elements = 22195
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 22195
----------------------------
Total number of nodes    = 22194
Total number of elements = 22195

real	0m39.779s
user	1m7.132s
sys	0m12.552s
+ status=0
+ set +x

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


=================================================
tess_MinQuad.py test;
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
+ python tess_MinQuad.py

==> Loading geometry from file "../../data/ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = riteWingSkin, index = 3
	Name = wingSpar1, index = 4
	Name = leftWingSkin, index = 5
	Name = wingTE, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = leadingEdge, index = 3
	Name = rootLeadingEdge, index = 4
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 299
Number of elements = 387
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 387
----------------------------
Total number of nodes    = 299
Total number of elements = 387
--> Total Elements 387

real	0m22.413s
user	1m7.191s
sys	2m17.950s
+ status=0
+ set +x

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


=================================================
tess_2k.py test;
+ python tess_2k.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

==> Loading geometry from file "../../data/ESP/wing3.csm"...
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3

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

real	0m20.821s
user	1m9.935s
sys	2m47.958s
+ status=0
+ set +x

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


=================================================
astros_1_ModalClamped.py test;
+ python astros_1_ModalClamped.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

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

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 235
Number of elements = 227
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes    = 235
Total number of elements = 227
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

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

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

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

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

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

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

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

Writing subElement types (if any) - appending mesh file

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

==> Running mASTROS...
Reading Astros OUT file - extracting Eigen-Values!
	Number of Eigen-Values = 9
	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

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

real	0m23.883s
user	1m11.650s
sys	2m45.236s
+ 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 /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

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

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
	Name = ribSupport, index = 6
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 2)
Getting surface mesh for body 2 (of 2)
Body 1 (of 2)
Number of nodes    = 235
Number of elements = 227
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 227
Body 2 (of 2)
Number of nodes    = 1
Number of elements = 1
Number of node elements          = 1
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 236
Total number of elements = 228
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

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

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

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

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

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

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

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

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

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

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

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

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

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

real	0m24.733s
user	1m8.921s
sys	2m5.885s
+ status=0
+ set +x

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


=================================================
astros_3_StaticClamped.py test;
+ python astros_3_StaticClamped.py
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log

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

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 235
Number of elements = 227
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes    = 235
Total number of elements = 227
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

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

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

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

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

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

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

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

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

Writing subElement types (if any) - appending mesh file

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

==> Running mASTROS...

--> Maximum displacements:
--> Tmax 43461.879146949635
--> T1max 738.595
--> T2max 3686.25
--> T3max 43363.8

real	0m28.458s
user	1m14.712s
sys	2m48.196s
+ status=0
+ set +x

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


=================================================
astros_4_Composite.py test;
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
+ python astros_4_Composite.py

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

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = wingSpar2, index = 1
	Name = wingRib, index = 2
	Name = wingSpar1, index = 3
	Name = leftWingSkin, index = 4
	Name = riteWingSkin, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = wingSpar2, index = 1
	Name = wingSpar1, index = 2
	Name = rootLeadingEdge, index = 3
Getting surface mesh for body 1 (of 1)
Body 1 (of 1)
Number of nodes    = 235
Number of elements = 227
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 0
Number of quadrilateral elements = 227
----------------------------
Total number of nodes    = 235
Total number of elements = 227
Mapping Csys attributes ................
	Number of unique Csys attributes = 2
	Name = leftWingSkin, index = 1
	Name = riteWingSkin, index = 2

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

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

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

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

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

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

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

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

Writing subElement types (if any) - appending mesh file

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

==> Running mASTROS...

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

real	0m35.384s
user	0m56.878s
sys	0m13.611s
+ status=0
+ set +x

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


=================================================
nastran_5_Flutter.py test;
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
+ python nastran_5_Flutter.py

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

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

Getting FEA coordinate systems.......
	Number of coordinate systems - 2
	Coordinate system name - leftWingSkin
	Coordinate system name - riteWingSkin
Mapping capsConstraint attributes ................
	Number of unique capsConstraint attributes = 1
	Name = rootConstraint, index = 1
Mapping capsLoad attributes ................
	Number of unique capsLoad attributes = 2
	Name = ritePointLoad, index = 1
	Name = leftPointLoad, index = 2
Mapping capsBound attributes ................
	Number of unique capsBound attributes = 4
	Name = upperWing, index = 1
	Name = lowerWing, index = 2
	Name = leftTip, index = 3
	Name = riteTip, index = 4
Mapping capsConnect attributes ................
	Number of unique capsConnect attributes = 0
Mapping capsResponse attributes ................
	Number of unique capsResponse attributes = 0
Mapping capsReference attributes ................
	Number of unique capsReference attributes = 0
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 6
	Name = Wing, index = 1
	Name = wingSpar2, index = 2
	Name = wingRib, index = 3
	Name = riteWingSkin, index = 4
	Name = wingSpar1, index = 5
	Name = leftWingSkin, index = 6
Setting FEA Data
	Mesh for body = 0
	Number of nodal coordinates = 11
	Number of elements = 6
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 6
Setting FEA Data
	Mesh for body = 1
	Number of nodal coordinates = 11
	Number of elements = 6
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 6
Setting FEA Data
	Mesh for body = 2
	Number of nodal coordinates = 11
	Number of elements = 6
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 6
Setting FEA Data
	Mesh for body = 3
	Number of nodal coordinates = 939
	Number of elements = 1094
	Elemental Nodes = 0
	Elemental Rods  = 0
	Elemental Tria3 = 0
	Elemental Quad4 = 1094
Combining multiple FEA meshes!
	Combined Number of nodal coordinates = 972
	Combined Number of elements = 1112
	Combined Elemental Nodes = 0
	Combined Elemental Rods  = 0
	Combined Elemental Tria3 = 0
	Combined Elemental Quad4 = 1112
Getting vortex lattice surface data
	VLM surface name - upperWing
	Done getting vortex lattice surface data

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

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

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

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

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

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

Writing subElement types (if any) - appending mesh file

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

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

real	0m33.294s
user	1m3.802s
sys	0m45.317s
+ status=0
+ set +x

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


=================================================
aeroelastic_2_Iterative_SU2_Astros.py test;
+ tee -a /jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
+ python aeroelastic_2_Iterative_SU2_Astros.py
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory
 Information: Dynamic Loader for scribeWake.so not found
              scribeWake.so: cannot open shared object file: No such file or directory

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

Getting mesh sizing parameters
	Mesh sizing name - Farfield
	Mesh sizing name - leftWing
	Mesh sizing name - riteWing
	Done getting mesh sizing parameters
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.6
AFLR2    : Version Date   11/20/22 @ 09:21PM
AFLR2    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR2    : Compile Date   03/14/23 @ 08:39PM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 11.3.17
AFLR4    : Version Date   03/03/23 @ 03:12PM
AFLR4    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR4    : Compile Date   03/14/23 @ 08:40PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.23
EGADS    : OpenCASCADE Version 7.4.1
EGADS    : ---------------------------------------

EGADS    : EGADS CAD Geometry Setup

EGADS    : Model has 2 Active Bodies

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

EGADS    : Check Grid BCs

EGADS    : Grid BCs are OK

EGADS    : Face Neighbor-Faces Information

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

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

EGADS    : Face Edges Information

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

EGADS    : Face Loops Information

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

EGADS    : Loop Edges Information

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

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

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

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

EGADS    : Node Information

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

AFLR4    : Surface Mesh Spacing Setup

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

AFLR4    : Geometry Definition Information

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

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

AFLR4    : Surface Grid Generation

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

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

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

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

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

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

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

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

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

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

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

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

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

AFLR4    : Curvature BG Surface Grid Generation

AFLR4    : Nodes, Faces      =      3847      7686

AFLR4    : Surface Grid Generation

AFLR4    : Generate optimal mesh on surface definition 1
AFLR2    : Nodes, Trias,Quads=      6118     11925         0
AFLR4    : Nodes, Trias,Quads=      2408      4505         0

AFLR4    : Generate optimal mesh on surface definition 2
AFLR2    : Nodes, Trias,Quads=      5960     11610         0
AFLR4    : Nodes, Trias,Quads=      2296      4282         0

AFLR4    : Generate optimal mesh on surface definition 3
AFLR2    : Nodes, Trias,Quads=       147       230         0
AFLR4    : Nodes, Trias,Quads=       131       198         0

AFLR4    : Generate optimal mesh on surface definition 4
AFLR2    : Nodes, Trias,Quads=      6173     12035         0
AFLR4    : Nodes, Trias,Quads=      2395      4479         0

AFLR4    : Generate optimal mesh on surface definition 5
AFLR2    : Nodes, Trias,Quads=      6053     11796         0
AFLR4    : Nodes, Trias,Quads=      2292      4274         0

AFLR4    : Generate optimal mesh on surface definition 6
AFLR2    : Nodes, Trias,Quads=       147       230         0
AFLR4    : Nodes, Trias,Quads=       131       198         0

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

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

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

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

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

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

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      9290     18572      1526

OVERALL  : CPU Time          =     0.475   seconds
Body 1 (of 2)
Number of nodes    = 8970
Number of elements = 17936
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17936
Number of quadrilateral elements = 0
Body 2 (of 2)
Number of nodes    = 320
Number of elements = 636
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 636
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 9290
Total number of elements = 18572
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = leftWing, index = 1
	Name = riteWing, index = 2
	Name = Farfield, index = 3
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = Wing, index = 1
	Name = Farfield, index = 2
Getting volume mesh
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.6
AFLR2    : Version Date   11/20/22 @ 09:21PM
AFLR2    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR2    : Compile Date   03/14/23 @ 08:39PM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 11.3.17
AFLR4    : Version Date   03/03/23 @ 03:12PM
AFLR4    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR4    : Compile Date   03/14/23 @ 08:40PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.23
EGADS    : OpenCASCADE Version 7.4.1
EGADS    : ---------------------------------------

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      9290     18572      1526
 
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
 
UG PARAM : mrecm                       = 3         
UG PARAM : mrecqm                      = 3         
 
UG PARAM : SETTING INPUT PARAMETERS FROM ARGUMENT VECTOR
 
UG PARAM : mrecm                       = 3         
UG PARAM : mrecqm                      = 3         
UG PARAM : mpfrmt                      = 0         
 
AFLR3    : ---------------------------------------
AFLR3    : AFLR3 LIBRARY
AFLR3    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR3    : TETRAHEDRAL GRID GENERATOR
AFLR3    : Version Number 16.32.39
AFLR3    : Version Date   03/10/23 @ 04:32PM
AFLR3    : Compile OS     Linux 3.10.0-1160.88.1.el7.x86_64 x86_64
AFLR3    : Compile Date   03/14/23 @ 08:40PM
AFLR3    : Copyright 1994-2021, D.L. Marcum
AFLR3    : ---------------------------------------
 
AFLR3 IC : INPUT SURFACE GRID CHECK
 
AFLR3 IC : Nodes, Elements   =      9290         0

UG3      : Boundary Conditions

UG3      :  B-Face ID            Boundary Condition
UG3      :          1                         Solid
UG3      :          2                         Solid
UG3      :          3                         Solid
UG3      :          4                         Solid
UG3      :          5                         Solid
UG3      :          6                         Solid
UG3      :          7                      FarField
UG3      :          8                      FarField
UG3      :          9                      FarField
UG3      :         10                      FarField
UG3      :         11                      FarField
UG3      :         12                      FarField
 
AFLR3    : CPU Time          =     0.020   seconds
 
AFLR3 IG : INITIAL VOLUME GRID GENERATION
 
AFLR3 IG : Nodes, Elements   =      9290         0
AFLR3 IG : Nodes, Elements   =         8        10
AFLR3 IG : Nodes, Elements   =      1860     12646
AFLR3 IG : Nodes, Elements   =      3720     25971
AFLR3 IG : Nodes, Elements   =      5580     39697
AFLR3 IG : Nodes, Elements   =      7440     54213
AFLR3 IG : Nodes, Elements   =      9297     69672
AFLR3 IG : Nodes, Elements   =      9297     69492
AFLR3 IG : Nodes, Elements   =      9290     42442
AFLR3 IG : Nodes, Elements   =      9290     42501
AFLR3 IG : Nodes, Elements   =      9290     30785
AFLR3 IG : Nodes, Elements   =      9290     28628
 
AFLR3    : CPU Time          =     0.266   seconds
 
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
 
AFLR3 GG : Nodes, Elements   =      9290     28628
AFLR3 GG : Nodes, Elements   =     13561     41513
AFLR3 GG : Nodes, Elements   =     13561     58358
AFLR3 GG : Nodes, Elements   =     13561     53657
AFLR3 GG : Nodes, Elements   =     17117     64735
AFLR3 GG : Nodes, Elements   =     17117     78808
AFLR3 GG : Nodes, Elements   =     17117     74279
AFLR3 GG : Nodes, Elements   =     20675     85292
AFLR3 GG : Nodes, Elements   =     20675     99081
AFLR3 GG : Nodes, Elements   =     20675     94981
AFLR3 GG : Nodes, Elements   =     24337    106153
AFLR3 GG : Nodes, Elements   =     24337    120869
AFLR3 GG : Nodes, Elements   =     24337    116773
AFLR3 GG : Nodes, Elements   =     28106    128236
AFLR3 GG : Nodes, Elements   =     28106    142965
AFLR3 GG : Nodes, Elements   =     28106    139010
AFLR3 GG : Nodes, Elements   =     31766    150079
AFLR3 GG : Nodes, Elements   =     31766    164489
AFLR3 GG : Nodes, Elements   =     31766    160588
AFLR3 GG : Nodes, Elements   =     35380    171500
AFLR3 GG : Nodes, Elements   =     35380    185811
AFLR3 GG : Nodes, Elements   =     35380    182124
AFLR3 GG : Nodes, Elements   =     38823    192508
AFLR3 GG : Nodes, Elements   =     38823    206006
AFLR3 GG : Nodes, Elements   =     38823    202470
AFLR3 GG : Nodes, Elements   =     42134    212447
AFLR3 GG : Nodes, Elements   =     42134    225390
AFLR3 GG : Nodes, Elements   =     42134    222178
AFLR3 GG : Nodes, Elements   =     45345    231848
AFLR3 GG : Nodes, Elements   =     45345    244494
AFLR3 GG : Nodes, Elements   =     45345    241207
AFLR3 GG : Nodes, Elements   =     48398    250392
AFLR3 GG : Nodes, Elements   =     48398    262281
AFLR3 GG : Nodes, Elements   =     48398    259327
AFLR3 GG : Nodes, Elements   =     51273    267969
AFLR3 GG : Nodes, Elements   =     51273    279340
AFLR3 GG : Nodes, Elements   =     51273    276462
AFLR3 GG : Nodes, Elements   =     54042    284789
AFLR3 GG : Nodes, Elements   =     54042    295506
AFLR3 GG : Nodes, Elements   =     54042    292883
AFLR3 GG : Nodes, Elements   =     56636    300683
AFLR3 GG : Nodes, Elements   =     56636    310952
AFLR3 GG : Nodes, Elements   =     56636    308342
AFLR3 GG : Nodes, Elements   =     59123    315811
AFLR3 GG : Nodes, Elements   =     59123    325722
AFLR3 GG : Nodes, Elements   =     59123    323181
AFLR3 GG : Nodes, Elements   =     61483    330272
AFLR3 GG : Nodes, Elements   =     61483    339606
AFLR3 GG : Nodes, Elements   =     61483    337245
AFLR3 GG : Nodes, Elements   =     63678    343841
AFLR3 GG : Nodes, Elements   =     63678    352418
AFLR3 GG : Nodes, Elements   =     63678    350277
AFLR3 GG : Nodes, Elements   =     65758    356528
AFLR3 GG : Nodes, Elements   =     65758    364558
AFLR3 GG : Nodes, Elements   =     65758    362578
AFLR3 GG : Nodes, Elements   =     67790    368681
AFLR3 GG : Nodes, Elements   =     67790    376603
AFLR3 GG : Nodes, Elements   =     67790    374718
AFLR3 GG : Nodes, Elements   =     69606    380169
AFLR3 GG : Nodes, Elements   =     69606    387298
AFLR3 GG : Nodes, Elements   =     69606    385523
AFLR3 GG : Nodes, Elements   =     71286    390568
AFLR3 GG : Nodes, Elements   =     71286    397091
AFLR3 GG : Nodes, Elements   =     71286    395493
AFLR3 GG : Nodes, Elements   =     72871    400253
AFLR3 GG : Nodes, Elements   =     72871    406495
AFLR3 GG : Nodes, Elements   =     72871    404928
AFLR3 GG : Nodes, Elements   =     74289    409183
AFLR3 GG : Nodes, Elements   =     74289    414668
AFLR3 GG : Nodes, Elements   =     74289    413342
AFLR3 GG : Nodes, Elements   =     75656    417447
AFLR3 GG : Nodes, Elements   =     75656    422806
AFLR3 GG : Nodes, Elements   =     75656    421489
AFLR3 GG : Nodes, Elements   =     76889    425188
AFLR3 GG : Nodes, Elements   =     76889    430052
AFLR3 GG : Nodes, Elements   =     76889    428849
AFLR3 GG : Nodes, Elements   =     78048    432330
AFLR3 GG : Nodes, Elements   =     78048    436850
AFLR3 GG : Nodes, Elements   =     78048    435708
AFLR3 GG : Nodes, Elements   =     79141    438988
AFLR3 GG : Nodes, Elements   =     79141    443321
AFLR3 GG : Nodes, Elements   =     79141    442273
AFLR3 GG : Nodes, Elements   =     80177    445384
AFLR3 GG : Nodes, Elements   =     80177    449363
AFLR3 GG : Nodes, Elements   =     80177    448421
AFLR3 GG : Nodes, Elements   =     81132    451286
AFLR3 GG : Nodes, Elements   =     81132    455027
AFLR3 GG : Nodes, Elements   =     81132    454114
AFLR3 GG : Nodes, Elements   =     81965    456616
AFLR3 GG : Nodes, Elements   =     81965    459966
AFLR3 GG : Nodes, Elements   =     81965    459099
AFLR3 GG : Nodes, Elements   =     82658    461179
AFLR3 GG : Nodes, Elements   =     82658    463902
AFLR3 GG : Nodes, Elements   =     82658    463198
AFLR3 GG : Nodes, Elements   =     83226    464902
AFLR3 GG : Nodes, Elements   =     83226    467218
AFLR3 GG : Nodes, Elements   =     83226    466581
AFLR3 GG : Nodes, Elements   =     83659    467880
AFLR3 GG : Nodes, Elements   =     83659    469692
AFLR3 GG : Nodes, Elements   =     83659    469158
AFLR3 GG : Nodes, Elements   =     83947    470023
AFLR3 GG : Nodes, Elements   =     83947    471204
AFLR3 GG : Nodes, Elements   =     83947    470847
AFLR3 GG : Nodes, Elements   =     84133    471405
AFLR3 GG : Nodes, Elements   =     84133    472156
AFLR3 GG : Nodes, Elements   =     84133    471928
AFLR3 GG : Nodes, Elements   =     84231    472222
AFLR3 GG : Nodes, Elements   =     84231    472634
AFLR3 GG : Nodes, Elements   =     84231    472491
AFLR3 GG : Nodes, Elements   =     84273    472617
AFLR3 GG : Nodes, Elements   =     84273    472798
AFLR3 GG : Nodes, Elements   =     84273    472740
AFLR3 GG : Nodes, Elements   =     84281    472764
AFLR3 GG : Nodes, Elements   =     84281    472792
AFLR3 GG : Nodes, Elements   =     84281    472781
AFLR3 GG : Nodes, Elements   =     84287    472799
AFLR3 GG : Nodes, Elements   =     84287    472813
AFLR3 GG : Nodes, Elements   =     84287    472807
 
AFLR3    : CPU Time          =     4.092   seconds
 
AFLR3 QI : QUALITY IMPROVEMENT
 
AFLR3 QI : Nodes, Elements   =     84287    472807
AFLR3 QI : Nodes, Elements   =     83845    470306
AFLR3 QI : Nodes, Elements   =     83783    469957
AFLR3 QI : Nodes, Elements   =     83774    469906
AFLR3 QI : Nodes, Elements   =     83774    471765
AFLR3 QI : Nodes, Elements   =     83774    469695
AFLR3 QI : Nodes, Elements   =     83774    468779
AFLR3 QI : Nodes, Elements   =     83774    469030
AFLR3 QI : Nodes, Elements   =     83774    468600
AFLR3 QI : Nodes, Elements   =     83774    468491
AFLR3 QI : Nodes, Elements   =     83774    468696
AFLR3 QI : Nodes, Elements   =     83774    468475
AFLR3 QI : Nodes, Elements   =     83774    468435
AFLR3 QI : Nodes, Elements   =     83774    468615
AFLR3 QI : Nodes, Elements   =     83774    468429
AFLR3 QI : Nodes, Elements   =     83774    468397
AFLR3 QI : Nodes, Elements   =     83774    468606
AFLR3 QI : Nodes, Elements   =     83774    468421
AFLR3 QI : Nodes, Elements   =     83774    468402
AFLR3 QI : Nodes, Elements   =     83775    468406
AFLR3 QI : Nodes, Elements   =     83775    468587
AFLR3 QI : Nodes, Elements   =     83775    468408
AFLR3 QI : Nodes, Elements   =     83775    468401
AFLR3 QI : Nodes, Elements   =     83775    468610
AFLR3 QI : Nodes, Elements   =     83775    468402
AFLR3 QI : Nodes, Elements   =     83775    468381
 
AFLR3    : CPU Time          =     1.671   seconds
 
AFLR3    : DONE

UG3      : DIHEDRAL ANGLE CHECK

UG3      : No. Tet Elems     =    468381
UG3      : Min, Max Ang      =     13.82     158.3
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     =    468381
UG3      : Min Vol           =  8.95e-07
UG3      : Average Vol       =      7.94
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     =    468381
UG3      : Min, Max Q        =      0.26         1
UG3      : Average Q         =     0.902
UG3      : No. Q<       0.1  =         0
UG3      : No. Q<      0.01  =         0

OVERALL  : CPU Time          =     6.189   seconds

UG3      : DIHEDRAL ANGLE CHECK

UG3      : No. Tet Elems     =    468381
UG3      : Min, Max Ang      =     13.82     158.3
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     =    468381
UG3      : Min Vol           =  8.95e-07
UG3      : Average Vol       =      7.94
UG3      : Total-Tet-Vol     =  3.72e+06
UG3      : No. Vol<TOL       =         0

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

UG3      : No. Tet Elems     =    468381
UG3      : Min, Max Q        =     0.383         1
UG3      : Average Q         =     0.874
UG3      : No. Q<       0.1  =         0
UG3      : No. Q<      0.01  =         0

UG3      : CPU Time          =     0.000   seconds

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.23
EGADS    : OpenCASCADE Version 7.4.1
EGADS    : ---------------------------------------

EGADS    : CREATE EGADS TESS FROM AFLR3 DATA

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

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

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

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

EGADS    : EGADS TESS CREATED

EGADS    : CHECK TESS GLOBAL FACE NODE MAP

EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 1
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 2
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 3
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 4
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 5
EGADS    : CHECKING NODE MAP FOR BODY 0 FACE 6
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 7
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 8
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 9
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 10
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 11
EGADS    : CHECKING NODE MAP FOR BODY 1 FACE 12
Volume mesh:
	Number of nodes          = 83775
	Number of elements       = 486953
	Number of triangles      = 18572
	Number of quadrilatarals = 0
	Number of tetrahedrals   = 468381
	Number of pyramids       = 0
	Number of prisms         = 0
	Number of hexahedrals    = 0
No project name ("Proj_Name") provided - A volume mesh will not be written out

Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Farfield
	Boundary condition name - Wing
	Done getting CFD boundary conditions
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.4.0 "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 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

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

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

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

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

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

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

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

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

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

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

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
83775 grid points.
468381 volume elements.
2 surface markers.
17936 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
468381 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: 20.6394. Standard deviation K: 49.3925.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        47.2388|         86.636|
|     CV Face Area Aspect Ratio|        1.07945|        107.626|
|           CV Sub-Volume Ratio|              1|        835.999|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     83775|    1/1.00|        10|
|         1|     13821|    1/6.06|   8.22684|
|         2|      2125|     1/6.5|   6.61095|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5583 m^2.
Area projection in the x-plane = 1.53011 m^2, y-plane = 0.868549 m^2, z-plane = 9.83638 m^2.
Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399868 m.
Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0329598 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.

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

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

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

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

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

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  3.1599e+00|   -1.769868|    0.448506|    0.049654|    3.699238|   -0.549589|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  3.1092e+00|   -1.514606|    0.839346|    0.462880|    3.962010|   -0.289362|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  3.0818e+00|   -1.526763|    0.926179|    0.740347|    3.939565|    1.925842|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  3.0624e+00|   -1.606192|    0.945796|    0.806951|    3.854348|   -8.538088|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  3.0572e+00|   -1.480946|    0.895276|    0.699471|    3.988747|   -5.572881|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.48095|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticIterative.dat|

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

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

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

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

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

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

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

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

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

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

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

Getting FEA analyses.......
	Number of analyses - 1
	Analysis name - Default
	Done getting FEA analyses
 CAPS Info: Reparameterization Bound -> upperWing -- nu, nv = 129 129
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 8970
 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.249086e+09, tgt = 6.249086e+09, diff = 2.904410e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 8970
 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.101315e+09, tgt = 6.101315e+09, diff = 1.479870e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 8970
 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.122063e+07, tgt = 6.122063e+07, diff = 7.450581e-09
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 8970
 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.122314e+07, tgt = 6.122314e+07, diff = 0.000000e+00
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)

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

Writing subElement types (if any) - appending mesh file

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


Running mASTROS......

==> Running ASTROS post-analysis...

==> Running SU2 pre-analysis...
Writing boundary flags
 - bcProps.surfaceProp[0].surfaceType = 3
 - bcProps.surfaceProp[1].surfaceType = 1
Done boundary flags
Writing SU2 data transfer files
Writing SU2 Motion File - aeroelasticIterative_motion.dat
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.4.0 "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 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

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

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


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

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_1|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_2|
+-----------------------------------------------------------------------+
Three dimensional problem.
83775 grid points.
468381 volume elements.
2 surface markers.
17936 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
468381 tetrahedra.

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

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

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

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


----------------------- 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 30.004525 seconds on 1 core.

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


-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.4.0 "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 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

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

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

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

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

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

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

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

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

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

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

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
83775 grid points.
468381 volume elements.
2 surface markers.
17936 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
468381 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: 20.6394. Standard deviation K: 49.3925.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        47.2388|         86.636|
|     CV Face Area Aspect Ratio|        1.07945|        107.626|
|           CV Sub-Volume Ratio|              1|        835.999|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     83775|    1/1.00|        10|
|         1|     13821|    1/6.06|   8.22684|
|         2|      2125|     1/6.5|   6.61095|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5583 m^2.
Area projection in the x-plane = 1.53011 m^2, y-plane = 0.868549 m^2, z-plane = 9.83638 m^2.
Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399868 m.
Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0329598 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.

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

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

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

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

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

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  3.1720e+00|   -1.769868|    0.448506|    0.049654|    3.699238|   -0.549589|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  3.1197e+00|   -1.514606|    0.839346|    0.462880|    3.962010|   -0.289362|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  3.1667e+00|   -1.526763|    0.926179|    0.740347|    3.939565|    1.925842|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  3.1325e+00|   -1.606192|    0.945796|    0.806951|    3.854348|   -8.538088|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  3.1101e+00|   -1.480946|    0.895276|    0.699471|    3.988747|   -5.572881|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.48095|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_aeroelasticIterative.dat|

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

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

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

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

------------------------- 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 = 8970
 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.249086e+09, tgt = 6.249086e+09, diff = 2.904410e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 8970
 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.101315e+09, tgt = 6.101315e+09, diff = 1.479870e+01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 8970
 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.122063e+07, tgt = 6.122063e+07, diff = 7.450581e-09
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 8970
 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.122314e+07, tgt = 6.122314e+07, diff = 0.000000e+00
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)

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

Writing subElement types (if any) - appending mesh file

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


Running mASTROS......

==> Running ASTROS post-analysis...

real	2m45.828s
user	3m1.059s
sys	0m18.559s
+ status=0
+ set +x

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


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

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

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

All tests pass!

[GNU C Compiler (gcc)] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64')
[Clang] Skipping post processing
[Clang] No filter has been set, publishing all 0 issues
[Clang] Repository miner is not configured, skipping repository mining
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64')
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/training/LINUX64')
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.4,CAPS/training,LINUX64,reynolds)
[Static Analysis] Using reference build 'ESP_UndefinedCaps/CASREV=7.4,ESPTEST=CAPS/training,ESP_ARCH=LINUX64,buildnode=reynolds #176' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 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=7.4,ESPTEST=CAPS/training,ESP_ARCH=LINUX64,buildnode=reynolds #178'.
[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