Console Output

Skipping 2,227 KB.. Full Log
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
146129 grid points.
825319 volume elements.
2 surface markers.
25868 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
825319 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: 5.96352e+10.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 25.1238. Mean K: 1.30702. Standard deviation K: 3.04293.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|         50.934|          86.73|
|     CV Face Area Aspect Ratio|        1.02773|        131.994|
|           CV Sub-Volume Ratio|        1.04037|        855.777|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|    146129|    1/1.00|        10|
|         1|     23999|    1/6.09|   8.21442|
|         2|      3650|    1/6.58|    6.5771|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 97.6729 m.
Wetted area = 8684.95 m^2.
Area projection in the x-plane = 678.503 m^2, y-plane = 443.208 m^2, z-plane = 4163.51 m^2.
Max. coordinate in the x-direction = 127.552 m, y-direction = 97.6729 m, z-direction = 7.71806 m.
Min. coordinate in the x-direction = 54 m, y-direction = -97.6729 m, z-direction = -5.479 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker 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|  6.0133e+00|    0.936995|    3.213583|    2.934955|    6.419840|   -0.377900|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  5.9315e+00|    1.006321|    3.498820|    3.145318|    6.507595|    0.088151|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  5.8988e+00|    1.079554|    3.620951|    3.393924|    6.570727|    1.643092|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  6.1092e+00|    1.159272|    3.739303|    3.531651|    6.646057|    7.067347|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  6.1364e+00|    1.220896|    3.827792|    3.616074|    6.713641|   37.425264|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|        1.2209|         < -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 =  0.322644 Cd =  0.008621
--> Cmx =  -6.4e-05 Cmy =  -0.052982 Cmz =  1.1e-05
--> Cx =  0.002989 Cy =  -8.2e-05 Cz =  0.322745

real	0m59.394s
user	0m56.414s
sys	0m3.330s
+ 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_RegCaps/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_RegCaps/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_RegCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/ESP/wing3.csm:104]]
        SELECT specified nonexistant Edge
    --> catching signal -223 (edge_not_found)

real	0m10.817s
user	0m19.107s
sys	1m55.173s
+ 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_RegCaps/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_RegCaps/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	0m10.255s
user	0m20.257s
sys	1m56.230s
+ status=0
+ set +x

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


=================================================
tess_3_Params.py test;
+ python tess_3_Params.py
+ tee -a /jenkins/workspace/ESP_RegCaps/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_RegCaps/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	0m9.705s
user	0m18.249s
sys	1m54.493s
+ status=0
+ set +x

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


=================================================
tess_4_Params.py test;
+ python tess_4_Params.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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	0m10.338s
user	0m20.220s
sys	1m55.208s
+ status=0
+ set +x

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


=================================================
tess_5_Params.py test;
+ python tess_5_Params.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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	0m12.034s
user	0m26.650s
sys	1m55.512s
+ status=0
+ set +x

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


=================================================
tess_6_TriQuad.py test;
+ python tess_6_TriQuad.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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_RegCaps/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	0m17.504s
user	0m26.996s
sys	1m55.238s
+ status=0
+ set +x

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


=================================================
tess_7_MeshSizing.py test;
+ python tess_7_MeshSizing.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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	0m11.536s
user	0m21.999s
sys	1m57.646s
+ status=0
+ set +x

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


=================================================
tess_8_MeshSizing.py test;
+ python tess_8_MeshSizing.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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	0m12.450s
user	0m21.529s
sys	1m47.130s
+ status=0
+ set +x

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


=================================================
tess_MinQuad.py test;
+ python tess_MinQuad.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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	0m10.700s
user	0m18.865s
sys	1m47.080s
+ status=0
+ set +x

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


=================================================
tess_2k.py test;
+ python tess_2k.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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	0m11.008s
user	0m18.400s
sys	1m44.679s
+ status=0
+ set +x

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


=================================================
astros_1_ModalClamped.py test;
+ python astros_1_ModalClamped.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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	0m11.470s
user	0m18.255s
sys	1m39.718s
+ status=0
+ set +x

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


=================================================
astros_2_ModalSupport.py test;
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/CAPS/training/LINUX64/CAPS/training/training.log
+ python astros_2_ModalSupport.py

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

==> Running ASTROS pre-analysis...
ERROR:: (edge_not_found) in Branch Brch_000207 at [[/jenkins/workspace/ESP_RegCaps/7.4/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	0m11.005s
user	0m16.734s
sys	1m24.086s
+ status=0
+ set +x

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


=================================================
astros_3_StaticClamped.py test;
+ python astros_3_StaticClamped.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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	0m11.231s
user	0m18.832s
sys	1m55.500s
+ status=0
+ set +x

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


=================================================
astros_4_Composite.py test;
+ python astros_4_Composite.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/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	0m12.097s
user	0m19.987s
sys	1m54.710s
+ status=0
+ set +x

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


=================================================
nastran_5_Flutter.py test;
+ python nastran_5_Flutter.py
+ tee -a /jenkins/workspace/ESP_RegCaps/7.4/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 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	0m11.009s
user	0m18.949s
sys	1m55.226s
+ status=0
+ set +x

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


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

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

Getting mesh sizing parameters
	Mesh sizing name - Farfield
	Mesh sizing name - leftWing
	Mesh sizing name - riteWing
	Done getting mesh sizing parameters
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.3
AFLR2    : Version Date   06/09/22 @ 05:16PM
AFLR2    : Compile OS     Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR2    : Compile Date   06/13/22 @ 12:42PM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 10.22.23
AFLR4    : Version Date   07/14/22 @ 02:23PM
AFLR4    : Compile OS     Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR4    : Compile Date   07/19/22 @ 12:23AM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.22
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    : IER = Face Isolated Edge Refinement Flag
EGADS    : ER  = Face Edge Refinement Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.
EGADS    : SF  = Face Scale Factor
EGADS    :       Not applicable for Faces with a FarField Grid BC.

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

EGADS    : Face Edges Information

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

EGADS    : Face Loops Information

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

EGADS    : Loop Edges Information

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

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

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

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

EGADS    : Node Information

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

AFLR4    : Surface Mesh Spacing Setup

AFLR4    : Max Bounding Box Length     = 154.919
AFLR4    : Min Bounding Box Length     = 154.919
AFLR4    : Max Ref Bounding Box Length = 7.74597
AFLR4    : Min Ref Bounding Box Length = 0.433058
AFLR4    : Reference Length            = 6.45497
AFLR4    : BL Thickness                = 0
AFLR4    : FarField Spacing            = 21.0478
AFLR4    : Abs Min Surf Spacing        = 0.0161374
AFLR4    : Min Surf Spacing            = 0.0322749
AFLR4    : Max Surf Spacing            = 0.645497
AFLR4    : 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, Faces      =      1658      3135
AFLR4    : Nodes, Faces      =       983      1785

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

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

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

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

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

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

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

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

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

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

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

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

AFLR4    : Curvature BG Surface Grid Generation

AFLR4    : Nodes, Faces      =      3828      7648

AFLR4    : Surface Grid Generation

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

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

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

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

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

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

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

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

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

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

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

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

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

OVERALL  : CPU Time          =     0.308   seconds
Body 1 (of 2)
Number of nodes    = 9000
Number of elements = 17996
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 17996
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    = 9320
Total number of elements = 18632
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
Number of surface nodes - 9320
Number of surface elements - 18632
Getting volume mesh
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.3
AFLR2    : Version Date   06/09/22 @ 05:16PM
AFLR2    : Compile OS     Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR2    : Compile Date   06/13/22 @ 12:42PM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR4    : ---------------------------------------
AFLR4    : AFLR4 LIBRARY
AFLR4    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4    : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4    : Version Number 10.22.23
AFLR4    : Version Date   07/14/22 @ 02:23PM
AFLR4    : Compile OS     Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR4    : Compile Date   07/19/22 @ 12:23AM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.22
EGADS    : OpenCASCADE Version 7.4.1
EGADS    : ---------------------------------------

OVERALL  : CPU Time          =     0.095   seconds

DGEOM    : Add surface definitions to composite definition 0
DGEOM    : Glue composite surface definition 0
DGEOM    : Nodes,Faces,BEdges=      9320     18632      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 16.32.32
AFLR3    : Version Date   06/10/22 @ 01:15PM
AFLR3    : Compile OS     Linux 3.10.0-957.27.2.el7.x86_64 x86_64
AFLR3    : Compile Date   06/24/22 @ 03:12PM
AFLR3    : Copyright 1994-2021, D.L. Marcum
AFLR3    : ---------------------------------------
 
AFLR3 IC : INPUT SURFACE GRID CHECK
 
AFLR3 IC : Nodes, Elements   =      9320         0

UG3      : Boundary Conditions

UG3      :  B-Face ID            Boundary Condition
UG3      :          1                         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          =     0.027   seconds
 
AFLR3 IG : INITIAL VOLUME GRID GENERATION
 
AFLR3 IG : Nodes, Elements   =      9320         0
AFLR3 IG : Nodes, Elements   =         8        10
AFLR3 IG : Nodes, Elements   =      1866     12712
AFLR3 IG : Nodes, Elements   =      3732     26115
AFLR3 IG : Nodes, Elements   =      5598     39852
AFLR3 IG : Nodes, Elements   =      7464     54343
AFLR3 IG : Nodes, Elements   =      9327     69980
AFLR3 IG : Nodes, Elements   =      9327     69786
AFLR3 IG : Nodes, Elements   =      9327     64954
AFLR3 IG : Nodes, Elements   =      9327     63454
AFLR3 IG : Nodes, Elements   =      9327     63453
AFLR3 IG : Nodes, Elements   =      9320     36301
AFLR3 IG : Nodes, Elements   =      9320     42408
AFLR3 IG : Nodes, Elements   =      9320     30451
AFLR3 IG : Nodes, Elements   =      9320     28149
 
AFLR3    : CPU Time          =     0.532   seconds
 
AFLR3 GG : ISOTROPIC VOLUME GRID GENERATION
 
AFLR3 GG : Nodes, Elements   =      9320     28149
AFLR3 GG : Nodes, Elements   =     13699     41351
AFLR3 GG : Nodes, Elements   =     13699     58816
AFLR3 GG : Nodes, Elements   =     13699     54352
AFLR3 GG : Nodes, Elements   =     17428     65921
AFLR3 GG : Nodes, Elements   =     17428     80425
AFLR3 GG : Nodes, Elements   =     17428     75760
AFLR3 GG : Nodes, Elements   =     20984     86777
AFLR3 GG : Nodes, Elements   =     20984    100666
AFLR3 GG : Nodes, Elements   =     20984     96611
AFLR3 GG : Nodes, Elements   =     24684    107830
AFLR3 GG : Nodes, Elements   =     24684    122340
AFLR3 GG : Nodes, Elements   =     24684    118457
AFLR3 GG : Nodes, Elements   =     28452    129886
AFLR3 GG : Nodes, Elements   =     28452    144581
AFLR3 GG : Nodes, Elements   =     28452    140704
AFLR3 GG : Nodes, Elements   =     32050    151561
AFLR3 GG : Nodes, Elements   =     32050    165780
AFLR3 GG : Nodes, Elements   =     32050    162054
AFLR3 GG : Nodes, Elements   =     35624    172813
AFLR3 GG : Nodes, Elements   =     35624    186856
AFLR3 GG : Nodes, Elements   =     35624    183277
AFLR3 GG : Nodes, Elements   =     39078    193672
AFLR3 GG : Nodes, Elements   =     39078    207271
AFLR3 GG : Nodes, Elements   =     39078    203883
AFLR3 GG : Nodes, Elements   =     42377    213821
AFLR3 GG : Nodes, Elements   =     42377    226594
AFLR3 GG : Nodes, Elements   =     42377    223445
AFLR3 GG : Nodes, Elements   =     45504    232850
AFLR3 GG : Nodes, Elements   =     45504    245050
AFLR3 GG : Nodes, Elements   =     45504    242015
AFLR3 GG : Nodes, Elements   =     48506    251047
AFLR3 GG : Nodes, Elements   =     48506    262865
AFLR3 GG : Nodes, Elements   =     48506    259891
AFLR3 GG : Nodes, Elements   =     51402    268591
AFLR3 GG : Nodes, Elements   =     51402    279793
AFLR3 GG : Nodes, Elements   =     51402    277041
AFLR3 GG : Nodes, Elements   =     54104    285156
AFLR3 GG : Nodes, Elements   =     54104    295759
AFLR3 GG : Nodes, Elements   =     54104    293091
AFLR3 GG : Nodes, Elements   =     56634    300692
AFLR3 GG : Nodes, Elements   =     56634    310694
AFLR3 GG : Nodes, Elements   =     56634    308228
AFLR3 GG : Nodes, Elements   =     59086    315602
AFLR3 GG : Nodes, Elements   =     59086    325172
AFLR3 GG : Nodes, Elements   =     59086    322785
AFLR3 GG : Nodes, Elements   =     61398    329727
AFLR3 GG : Nodes, Elements   =     61398    338809
AFLR3 GG : Nodes, Elements   =     61398    336551
AFLR3 GG : Nodes, Elements   =     63531    342957
AFLR3 GG : Nodes, Elements   =     63531    351470
AFLR3 GG : Nodes, Elements   =     63531    349292
AFLR3 GG : Nodes, Elements   =     65523    355273
AFLR3 GG : Nodes, Elements   =     65523    363113
AFLR3 GG : Nodes, Elements   =     65523    361158
AFLR3 GG : Nodes, Elements   =     67367    366696
AFLR3 GG : Nodes, Elements   =     67367    373915
AFLR3 GG : Nodes, Elements   =     67367    372123
AFLR3 GG : Nodes, Elements   =     69121    377387
AFLR3 GG : Nodes, Elements   =     69121    384191
AFLR3 GG : Nodes, Elements   =     69121    382549
AFLR3 GG : Nodes, Elements   =     70709    387318
AFLR3 GG : Nodes, Elements   =     70709    393617
AFLR3 GG : Nodes, Elements   =     70709    392034
AFLR3 GG : Nodes, Elements   =     72154    396369
AFLR3 GG : Nodes, Elements   =     72154    401986
AFLR3 GG : Nodes, Elements   =     72154    400579
AFLR3 GG : Nodes, Elements   =     73538    404732
AFLR3 GG : Nodes, Elements   =     73538    410170
AFLR3 GG : Nodes, Elements   =     73538    408845
AFLR3 GG : Nodes, Elements   =     74833    412731
AFLR3 GG : Nodes, Elements   =     74833    417772
AFLR3 GG : Nodes, Elements   =     74833    416564
AFLR3 GG : Nodes, Elements   =     76063    420258
AFLR3 GG : Nodes, Elements   =     76063    424942
AFLR3 GG : Nodes, Elements   =     76063    423841
AFLR3 GG : Nodes, Elements   =     77160    427134
AFLR3 GG : Nodes, Elements   =     77160    431404
AFLR3 GG : Nodes, Elements   =     77160    430393
AFLR3 GG : Nodes, Elements   =     78190    433484
AFLR3 GG : Nodes, Elements   =     78190    437528
AFLR3 GG : Nodes, Elements   =     78190    436519
AFLR3 GG : Nodes, Elements   =     79146    439387
AFLR3 GG : Nodes, Elements   =     79146    443095
AFLR3 GG : Nodes, Elements   =     79146    442217
AFLR3 GG : Nodes, Elements   =     79942    444605
AFLR3 GG : Nodes, Elements   =     79942    447702
AFLR3 GG : Nodes, Elements   =     79942    446960
AFLR3 GG : Nodes, Elements   =     80589    448902
AFLR3 GG : Nodes, Elements   =     80589    451545
AFLR3 GG : Nodes, Elements   =     80589    450824
AFLR3 GG : Nodes, Elements   =     81070    452268
AFLR3 GG : Nodes, Elements   =     81070    454232
AFLR3 GG : Nodes, Elements   =     81070    453700
AFLR3 GG : Nodes, Elements   =     81370    454602
AFLR3 GG : Nodes, Elements   =     81370    455894
AFLR3 GG : Nodes, Elements   =     81370    455489
AFLR3 GG : Nodes, Elements   =     81531    455973
AFLR3 GG : Nodes, Elements   =     81531    456671
AFLR3 GG : Nodes, Elements   =     81531    456439
AFLR3 GG : Nodes, Elements   =     81590    456616
AFLR3 GG : Nodes, Elements   =     81590    456885
AFLR3 GG : Nodes, Elements   =     81590    456779
AFLR3 GG : Nodes, Elements   =     81613    456848
AFLR3 GG : Nodes, Elements   =     81613    456938
AFLR3 GG : Nodes, Elements   =     81613    456906
AFLR3 GG : Nodes, Elements   =     81617    456918
AFLR3 GG : Nodes, Elements   =     81617    456940
AFLR3 GG : Nodes, Elements   =     81617    456931
AFLR3 GG : Nodes, Elements   =     81619    456937
AFLR3 GG : Nodes, Elements   =     81619    456942
AFLR3 GG : Nodes, Elements   =     81619    456941
AFLR3 GG : Nodes, Elements   =     81622    456950
AFLR3 GG : Nodes, Elements   =     81622    456966
AFLR3 GG : Nodes, Elements   =     81622    456955
 
AFLR3    : CPU Time          =     4.314   seconds
 
AFLR3 QI : QUALITY IMPROVEMENT
 
AFLR3 QI : Nodes, Elements   =     81622    456955
AFLR3 QI : Nodes, Elements   =     81261    454894
AFLR3 QI : Nodes, Elements   =     81217    454646
AFLR3 QI : Nodes, Elements   =     81211    454613
AFLR3 QI : Nodes, Elements   =     81210    454607
AFLR3 QI : Nodes, Elements   =     81210    456522
AFLR3 QI : Nodes, Elements   =     81210    454482
AFLR3 QI : Nodes, Elements   =     81210    453617
AFLR3 QI : Nodes, Elements   =     81210    455109
AFLR3 QI : Nodes, Elements   =     81210    453586
AFLR3 QI : Nodes, Elements   =     81210    453541
AFLR3 QI : Nodes, Elements   =     81210    454958
AFLR3 QI : Nodes, Elements   =     81210    453566
AFLR3 QI : Nodes, Elements   =     81210    453541
AFLR3 QI : Nodes, Elements   =     81210    454925
AFLR3 QI : Nodes, Elements   =     81210    453553
AFLR3 QI : Nodes, Elements   =     81210    453531
AFLR3 QI : Nodes, Elements   =     81210    454909
AFLR3 QI : Nodes, Elements   =     81210    453548
AFLR3 QI : Nodes, Elements   =     81210    453527
AFLR3 QI : Nodes, Elements   =     81211    453531
AFLR3 QI : Nodes, Elements   =     81211    454906
AFLR3 QI : Nodes, Elements   =     81211    453550
AFLR3 QI : Nodes, Elements   =     81211    453534
AFLR3 QI : Nodes, Elements   =     81211    454897
AFLR3 QI : Nodes, Elements   =     81211    453544
AFLR3 QI : Nodes, Elements   =     81211    453531
 
AFLR3    : CPU Time          =     2.817   seconds
 
AFLR3 QRG: QUALITY GRID RE-GENERATION
 
AFLR3 QRG: Nodes, Elements   =     81211    453531
AFLR3 QRG: Nodes, Elements   =     81212    453532
 
AFLR3    : CPU Time          =     0.062   seconds
 
AFLR3    : DONE

UG3      : DIHEDRAL ANGLE CHECK

UG3      : No. Tet Elems     =    453532
UG3      : Min, Max Ang      =     8.048       164
UG3      : Average Angle     =      70.2
UG3      : No. Angle>160.0   =         4
UG3      : No. Angle>179.9   =         0

UG3      : VOL CHECK

UG3      : Total-Volume      =  3.72e+06

UG3      : No. Tet Elems     =    453532
UG3      : Min Vol           =  1.11e-06
UG3      : Average Vol       =       8.2
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     =    453532
UG3      : Min, Max Q        =     0.123         1
UG3      : Average Q         =     0.861
UG3      : No. Q<       0.1  =         0
UG3      : No. Q<      0.01  =         0

UG3      : DIHEDRAL ANGLE CHECK

UG3      : No. Tet Elems     =    453532
UG3      : Min, Max Ang      =     8.048       164
UG3      : Average Angle     =      70.2
UG3      : No. Angle>160.0   =         4
UG3      : No. Angle>179.9   =         0

UG3      : VOL CHECK

UG3      : Total-Volume      =  3.72e+06

UG3      : No. Tet Elems     =    453532
UG3      : Min Vol           =  1.11e-06
UG3      : Average Vol       =       8.2
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     =    453532
UG3      : Min, Max Q        =      0.24         1
UG3      : Average Q         =     0.845
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 1.22
EGADS    : OpenCASCADE Version 7.4.1
EGADS    : ---------------------------------------

OVERALL  : CPU Time          =     0.082   seconds

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
 
UG_IO    : OUTPUT GRID
 
UG_IO    : Writing Data
 
UG_IO    : Grid File Name    = /jenkins/workspace/ESP_RegCaps/7.4/CAPS/training/LINUX64/CAPS/training/data/session11/workDir_2_Aeroelastic_Iterative/Scratch/aflr3/aflr3_0.lb8.ugrid
UG_IO    : Quad Surface Faces=         0
UG_IO    : Tria Surface Faces=     18632
UG_IO    : Quad Int. Faces   =         0
UG_IO    : Tria Int. Faces   =    897748
UG_IO    : Nodes             =     81212
UG_IO    : Total Elements    =    453532
UG_IO    : Hex Elements      =         0
UG_IO    : Pent_5 Elements   =         0
UG_IO    : Pent_6 Elements   =         0
UG_IO    : Tet Elements      =    453532
 
UG_IO    : CPU Time          =     0.008   seconds
Volume mesh:
	Number of nodes = 81212
	Number of elements = 472164
	Number of triangles = 18632
	Number of quadrilatarals = 0
	Number of tetrahedrals = 453532
	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.
81212 grid points.
453532 volume elements.
2 surface markers.
17996 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
453532 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: 20.5059. Standard deviation K: 49.1995.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        49.1472|        85.0831|
|     CV Face Area Aspect Ratio|        1.02671|        146.013|
|           CV Sub-Volume Ratio|              1|        494.707|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     81212|    1/1.00|        10|
|         1|     13368|    1/6.08|   8.22066|
|         2|      2027|    1/6.59|   6.57547|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5565 m^2.
Area projection in the x-plane = 1.53007 m^2, y-plane = 0.868422 m^2, z-plane = 9.83485 m^2.
Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399868 m.
Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0329185 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker 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|  4.4907e+00|   -1.764878|    0.454105|    0.056364|    3.704228|   -0.551627|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  4.2509e+00|   -1.601678|    0.768552|    0.497187|    3.871933|   -0.295784|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  3.8477e+00|   -1.630268|    0.891975|    0.713693|    3.838956|    1.702462|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  3.8257e+00|   -1.744248|    0.878715|    0.743771|    3.718831|   -8.900276|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  3.8125e+00|   -1.696893|    0.776009|    0.664214|    3.767031|   -5.371341|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.69689|         < -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 = 9000
 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.247207e+09, tgt = 6.247207e+09, diff = 3.722477e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.100569e+09, tgt = 6.100569e+09, diff = 5.472136e-01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.124625e+07, tgt = 6.124625e+07, diff = 2.980232e-08
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.121854e+07, tgt = 6.121854e+07, diff = 3.874302e-07
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.
81212 grid points.
453532 volume elements.
2 surface markers.
17996 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
453532 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 26.386191 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)                                            |
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| 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.    |
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| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
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-------------------------------------------------------------------------

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.
81212 grid points.
453532 volume elements.
2 surface markers.
17996 boundary elements in index 0 (Marker = BC_1).
636 boundary elements in index 1 (Marker = BC_2).
453532 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: 20.5059. Standard deviation K: 49.1995.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        49.1472|        85.0831|
|     CV Face Area Aspect Ratio|        1.02671|        146.013|
|           CV Sub-Volume Ratio|              1|        494.707|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     81212|    1/1.00|        10|
|         1|     13368|    1/6.08|   8.22066|
|         2|      2027|    1/6.59|   6.57547|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 3.87298 m.
Wetted area = 20.5565 m^2.
Area projection in the x-plane = 1.53007 m^2, y-plane = 0.868422 m^2, z-plane = 9.83485 m^2.
Max. coordinate in the x-direction = 2.37421 m, y-direction = 3.87298 m, z-direction = 0.399868 m.
Min. coordinate in the x-direction = 0 m, y-direction = -3.87298 m, z-direction = -0.0329185 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker 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|  3.2323e+00|   -1.764878|    0.454105|    0.056364|    3.704228|   -0.551627|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  3.1765e+00|   -1.601678|    0.768552|    0.497187|    3.871933|   -0.295784|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  3.1530e+00|   -1.630268|    0.891975|    0.713693|    3.838956|    1.702462|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  3.1589e+00|   -1.744248|    0.878715|    0.743771|    3.718831|   -8.900276|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  3.1447e+00|   -1.696893|    0.776009|    0.664214|    3.767031|   -5.371341|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.69689|         < -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 = 9000
 CAPS Info: Bound 'upperWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.247207e+09, tgt = 6.247207e+09, diff = 3.722477e+00
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'lowerWing' Normalized Integrated 'Pressure'
            Rank 0: src = 6.100569e+09, tgt = 6.100569e+09, diff = 5.472136e-01
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'leftTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.124625e+07, tgt = 6.124625e+07, diff = 2.980232e-08
Reading SU2 AeroLoad File - surface_flow_aeroelasticIterative.csv
	Number of variables = 13
	Number of data points = 9000
 CAPS Info: Bound 'riteTip' Normalized Integrated 'Pressure'
            Rank 0: src = 6.121854e+07, tgt = 6.121854e+07, diff = 3.874302e-07
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	2m29.401s
user	2m34.888s
sys	1m57.752s
+ status=0
+ set +x

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


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

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

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

All tests pass!

[Execution node] check if [reynolds] is in [[windows10x64]]
Run condition [Execution node ] preventing perform for step [Execute Windows batch command]
[GNU C Compiler (gcc)] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/7.4/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_RegCaps/7.4/CAPS/training/LINUX64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/jenkins/workspace/ESP_RegCaps/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_RegCaps/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] 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_RegCaps/CASREV=7.4,ESPTEST=CAPS/training,ESP_ARCH=LINUX64,buildnode=reynolds #469' 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_RegCaps/CASREV=7.4,ESPTEST=CAPS/training,ESP_ARCH=LINUX64,buildnode=reynolds #470'.
[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