Console Output

Skipping 415 KB.. Full Log
AFLR2 GGp: Nodes, Faces      =       363       540
AFLR2 GGp: Nodes, Faces      =       536       886
AFLR2 GGp: Nodes, Faces      =       704      1222
AFLR2 GGp: Nodes, Faces      =       879      1572
AFLR2 GGp: Nodes, Faces      =      1056      1926
AFLR2 GGp: Nodes, Faces      =      1224      2262
AFLR2 GGp: Nodes, Faces      =      1388      2590
AFLR2 GGp: Nodes, Faces      =      1548      2910
AFLR2 GGp: Nodes, Faces      =      1705      3224
AFLR2 GGp: Nodes, Faces      =      1862      3538
AFLR2 GGp: Nodes, Faces      =      1990      3794
AFLR2 GGp: Nodes, Faces      =      2106      4026
AFLR2 GGp: Nodes, Faces      =      2192      4198
AFLR2 GGp: Nodes, Faces      =      2256      4326
AFLR2 GGp: Nodes, Faces      =      2300      4414
AFLR2 GGp: Nodes, Faces      =      2334      4482
AFLR2 GGp: Nodes, Faces      =      2360      4534
AFLR2 GGp: Nodes, Faces      =      2378      4570
AFLR2 GGp: Nodes, Faces      =      2390      4594
AFLR2 GGp: Nodes, Faces      =      2391      4596
 
AFLR2    : CPU Time          =     0.005   seconds
 
AFLR2 QI : QUALITY IMPROVEMENT
 
AFLR2 QI : Nodes, Faces      =      2391      4596
AFLR2 QI : Nodes, Faces      =      2391       232
AFLR2 QI : Nodes, Faces      =      2391      2182
AFLR2 QI : Nodes, Faces      =      2391      4596
AFLR2 QI : Nodes, Faces      =      2391       230
AFLR2 QI : Nodes, Faces      =      2391      2183
AFLR2 QI : Nodes, Faces      =      2391      4596
AFLR2 QI : Nodes, Faces      =      2391       286
AFLR2 QI : Nodes, Faces      =      2391      2155
AFLR2 QI : Nodes, Faces      =      2391      4596
AFLR2 QI : Nodes, Faces      =      2390       536
AFLR2 QI : Nodes, Faces      =      2390      2029
AFLR2 QI : Nodes, Faces      =      2390      4594
AFLR2 QI : Nodes, Faces      =      2390       296
AFLR2 QI : Nodes, Faces      =      2390      2149
AFLR2 QI : Nodes, Faces      =      2390      4594
AFLR2 QI : Nodes, Faces      =      2390       278
AFLR2 QI : Nodes, Faces      =      2390      2158
AFLR2 QI : Nodes, Faces      =      2390       278
AFLR2 QI : Nodes, Faces      =      2390      2158
 
AFLR2    : CPU Time          =     0.003   seconds
 
AFLR2    : DONE
 
UG_IO    : OUTPUT GRID
 
UG_IO    : Writing Data
 
UG_IO    : Grid File Name    = /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/cCAPS/FUN3D_AFRL2_Example/Scratch/runDirectory1/aflr2.lb8.ugrid
UG_IO    : Boundary Edges    =       186
UG_IO    : Nodes             =      2390
UG_IO    : Quad Faces        =      2158
UG_IO    : Tria Faces        =       278
 
UG_IO    : CPU Time          =     0.001   seconds
Number of nodes = 2390
Number of elements = 2622
Number of tris = 278
Number of quad = 2158
Getting CFD boundary conditions
	Boundary condition name - Airfoil
	Boundary condition name - TunnelWall
	Boundary condition name - InFlow
	Boundary condition name - OutFlow
	Boundary condition name - 2DSlice
	Done getting CFD boundary conditions
Python library was linked, but will not be used!

Surface mesh is not on y = 0.0 plane, FUN3D could fail during execution for this 2D mesh!!!
FUN3D expects 2D meshes be in the x-z plane... attempting to rotate mesh!
Swapping y and z coordinates!

Creating a 3D volume mesh from a 2D surface
	Number of Nodes =  4780
	Number of Prisms =  278
	Number of Hexahedral =  2158

Writing AFLR3 file ....
Finished writing AFLR3 file


Writing MAPBC file ....
Finished writing MAPBC file

Warning: The fun3d.nml file will be overwritten!
Writing fun3d.nml
 NOT Running fun3d!

real	0m3.564s
user	0m0.613s
sys	0m0.361s
+ status=0
+ set +x

=============================================
CAPS verification (using c-executables) case ./fun3dAFLR2Test passed (as expected)
=============================================


=================================================
+ echo './fun3dTetgenTest test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/cCAPSlog.txt
./fun3dTetgenTest test;
+ ./fun3dTetgenTest 0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/cCAPSlog.txt


Attention: fun3dTetgenTest is hard coded to look for ../csmData/cfdMultiBody.csm
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 4
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Wake, index = 3
	Name = Farfield, index = 4
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Wake, index = 3
	Name = Farfield, 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)
Body 1 (of 4)
Number of nodes    = 9607
Number of elements = 19210
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 19210
Number of quadrilateral elements = 0
Body 2 (of 4)
Number of nodes    = 6142
Number of elements = 12280
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 12280
Number of quadrilateral elements = 0
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value
Body 3 (of 4)
Number of nodes    = 2145
Number of elements = 4096
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 4096
Number of quadrilateral elements = 0
Body 4 (of 4)
Number of nodes    = 265
Number of elements = 526
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 526
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 18159
Total number of elements = 36112
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 4
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Wake, index = 3
	Name = Farfield, index = 4
Number of surface nodes - 18159
Number of surface elements - 36112
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000T1.00e-16
Delaunizing vertices...
Delaunay seconds:  0.410848
Creating surface mesh ...
Surface mesh seconds:  0.056741
Recovering boundaries...
Boundary recovery seconds:  0.204604
Removing exterior tetrahedra ...
Exterior tets removal seconds:  0.053626
Recovering Delaunayness...
Delaunay recovery seconds:  0.00051
Refining mesh...
Refinement seconds:  0.000826
Improving mesh...
Mesh improvement seconds:  0.000745
Jettisoning redundant points.

Writing nodes.
Writing edges.

Output seconds:  0.002309
Total running seconds:  0.731834

Statistics:

  Input points: 18159
  Input facets: 36112
  Input segments: 54264
  Input holes: 3
  Input regions: 0

  Mesh points: 0
  Mesh tetrahedra: 0
  Mesh faces: 0
  Mesh faces on exterior boundary: 0
  Mesh faces on input facets: 0
  Mesh edges on input segments: 0

Done meshing using TetGen!
Volume mesher did not preserve surface elements - data transfer will NOT be possible.
No project name ("Proj_Name") provided - A volume mesh will not be written out
Getting CFD boundary conditions
	Boundary condition name - Wing1
	Boundary condition name - Wing2
	Boundary condition name - Farfield
	Warning: No boundary condition specified for capsGroup Wake!
	Done getting CFD boundary conditions
Python library was linked, but will not be used!

Writing MAPBC file ....
Finished writing MAPBC file

Warning: The fun3d.nml file will be overwritten!
Writing fun3d.nml
Info: No recognized data transfer names found.
 NOT Running fun3d!

real	0m14.343s
user	0m10.738s
sys	0m0.212s
+ status=0
+ set +x

=============================================
CAPS verification (using c-executables) case ./fun3dTetgenTest passed (as expected)
=============================================


All tests pass!


=================================================
=================================================
++ '[' '!' -z '-L/Users/jenkins/util/ESP/Python/ESP_Python-3.9.13/lib -lpython3.9 -ldl -framework CoreFoundation' ']'
++ ./execute_PyTestRegression.sh CFD

=================================================
Using python : /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP_venv/bin/python
=================================================

Running.... CFD PyTests


=================================================
+ echo 'su2_and_AFLR2_NodeDist_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_and_AFLR2_NodeDist_PyTest.py test;
+ python -u su2_and_AFLR2_NodeDist_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5

Getting mesh sizing parameters
	Mesh sizing name - 2DSlice
	Mesh sizing name - Airfoil
	Mesh sizing name - InFlow
	Mesh sizing name - OutFlow
	Mesh sizing name - TunnelWall
	Done getting mesh sizing parameters
Getting 2D mesh for body 1 (of 1)
 
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     Darwin 20.6.0 arm64
AFLR2    : Compile Date   06/13/22 @ 10:43AM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR2 IC : INPUT DATA CHECK
 
AFLR2 IC : Nodes, Faces      =       224         0
 
AFLR2    : CPU Time          =     0.000   seconds
 
AFLR2 EG : EDGE GRID RE-GENERATION
 
AFLR2 EG : Nodes, Edges      =       224       224
 
AFLR2    : CPU Time          =     0.000   seconds
 
AFLR2 IG : INITIAL GRID GENERATION
 
AFLR2 IG : Nodes, Faces      =         0         2
AFLR2 IG : Nodes, Faces      =        46        94
AFLR2 IG : Nodes, Faces      =        92       186
AFLR2 IG : Nodes, Faces      =       138       278
AFLR2 IG : Nodes, Faces      =       184       370
AFLR2 IG : Nodes, Faces      =       196       394
AFLR2 IG : Nodes, Faces      =       224       450
AFLR2 IG : Nodes, Faces      =       228       450
AFLR2 IG : Nodes, Faces      =       224       224
 
AFLR2    : CPU Time          =     0.000   seconds
 
AFLR2 GG : FIELD GRID GENERATION
 
AFLR2 GG : Nodes, Faces      =       224       224
AFLR2 GG : Nodes, Faces      =       440       656
AFLR2 GG : Nodes, Faces      =       649      1074
AFLR2 GG : Nodes, Faces      =       853      1482
AFLR2 GG : Nodes, Faces      =      1050      1876
AFLR2 GG : Nodes, Faces      =      1238      2252
AFLR2 GG : Nodes, Faces      =      1421      2618
AFLR2 GG : Nodes, Faces      =      1594      2964
AFLR2 GG : Nodes, Faces      =      1760      3296
AFLR2 GG : Nodes, Faces      =      1915      3606
AFLR2 GG : Nodes, Faces      =      2063      3902
AFLR2 GG : Nodes, Faces      =      2202      4180
AFLR2 GG : Nodes, Faces      =      2314      4404
AFLR2 GG : Nodes, Faces      =      2423      4622
AFLR2 GG : Nodes, Faces      =      2528      4832
AFLR2 GG : Nodes, Faces      =      2634      5044
AFLR2 GG : Nodes, Faces      =      2732      5240
AFLR2 GG : Nodes, Faces      =      2831      5438
AFLR2 GG : Nodes, Faces      =      2927      5630
AFLR2 GG : Nodes, Faces      =      3018      5812
AFLR2 GG : Nodes, Faces      =      3109      5994
AFLR2 GG : Nodes, Faces      =      3202      6180
AFLR2 GG : Nodes, Faces      =      3295      6366
AFLR2 GG : Nodes, Faces      =      3386      6548
AFLR2 GG : Nodes, Faces      =      3464      6704
AFLR2 GG : Nodes, Faces      =      3535      6846
AFLR2 GG : Nodes, Faces      =      3594      6964
AFLR2 GG : Nodes, Faces      =      3639      7054
AFLR2 GG : Nodes, Faces      =      3671      7118
AFLR2 GG : Nodes, Faces      =      3691      7158
AFLR2 GG : Nodes, Faces      =      3705      7186
AFLR2 GG : Nodes, Faces      =      3712      7200
AFLR2 GG : Nodes, Faces      =      3715      7206
 
AFLR2    : CPU Time          =     0.004   seconds
 
AFLR2 QI : QUALITY IMPROVEMENT
 
AFLR2 QI : Nodes, Faces      =      3715      7206
 
AFLR2    : CPU Time          =     0.000   seconds
 
AFLR2    : DONE
 
UG_IO    : OUTPUT GRID
 
UG_IO    : Writing Data
 
UG_IO    : Grid File Name    = /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/SU2AFLR2NodeDistAnalysisTest/Scratch/aflr2/aflr2.lb8.ugrid
UG_IO    : Boundary Edges    =       224
UG_IO    : Nodes             =      3715
UG_IO    : Quad Faces        =         0
UG_IO    : Tria Faces        =      7206
 
UG_IO    : CPU Time          =     0.001   seconds
Number of nodes = 3715
Number of elements = 7430
Number of tris = 7206
Number of quad = 0

Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Airfoil
	Boundary condition name - InFlow
	Boundary condition name - OutFlow
	Boundary condition name - TunnelWall
	Warning: No boundary condition specified for capsGroup 2DSlice!
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "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: 0.4.
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 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_5.

Surface(s) plotted in the output file: BC_5, BC_2.
Input mesh file name: ../aflr2/aflr2.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: 10.
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_pyCAPS_SU2_aflr2.dat.
Surface file name: surface_flow_pyCAPS_SU2_aflr2.
Volume file name: flow_pyCAPS_SU2_aflr2.
Restart file name: restart_flow_pyCAPS_SU2_aflr2.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_5|
|                                   |                               BC_2|
+-----------------------------------------------------------------------+
|                     Inlet boundary|                               BC_4|
+-----------------------------------------------------------------------+
|                    Outlet boundary|                               BC_3|
+-----------------------------------------------------------------------+

-------------------- 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 ) -------------------
Two dimensional problem.
3715 grid points.
7206 volume elements.
4 surface markers.
98 boundary elements in index 0 (Marker = BC_2).
24 boundary elements in index 1 (Marker = BC_3).
24 boundary elements in index 2 (Marker = BC_4).
78 boundary elements in index 3 (Marker = BC_5).
7206 triangles.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 7206 TRIANGLE volume elements.
There has been a re-orientation of 224 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 999.917.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 177.06. Mean K: 1.97232. Standard deviation K: 13.0434.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        63.4343|             90|
|     CV Face Area Aspect Ratio|              1|        5.23543|
|           CV Sub-Volume Ratio|              1|        3.11804|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      3715|    1/1.00|        10|
|         1|      1048|    1/3.54|   7.96696|
|         2|       299|    1/3.51|    6.3832|
+-------------------------------------------+
Finding max control volume width.
Wetted area = 2.06136 m.
Area projection in the x-plane = 0.178383 m, y-plane = 0.994925 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.138389 m.
Min. coordinate in the x-direction = -0.000250564 m, y-direction = -0.0152 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_5 is NOT a single straight.
Boundary marker BC_2 is NOT a single straight.
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|        216054|             1|   m^2/s^2|        216054|
|            Velocity-X|       136.119|             1|       m/s|       136.119|
|            Velocity-Y|             0|             1|       m/s|             0|
|    Velocity Magnitude|       136.119|             1|       m/s|       136.119|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|           0.4|
+------------------------------------------------------------------------------+
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|  3.2701e-02|   -0.385358|    2.453598|    1.625650|    5.369499|    0.360386|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  2.9047e-02|   -0.521485|    2.079409|    1.371893|    4.965390|    1.182869|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  3.1028e-02|   -0.795894|    1.733901|    1.139977|    4.664635|    3.893206|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  3.2200e-02|   -0.885699|    1.481333|    1.013745|    4.332779|   14.565626|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  3.1558e-02|   -0.993750|    1.340252|    0.917512|    4.182929|  110.245147|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  3.1686e-02|   -1.110400|    1.172200|    0.857005|    3.936064| -495.837992|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  3.3287e-02|   -1.185766|    1.111335|    0.833878|    3.815560|  126.876277|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  3.3331e-02|   -1.253010|    1.087204|    0.820499|    3.761995|   40.129370|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  3.2534e-02|   -1.297506|    1.067370|    0.803440|    3.702559|   25.133461|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  3.2280e-02|   -1.307387|    1.040693|    0.767965|    3.668428|   21.072343|

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

Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.30739|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_pyCAPS_SU2_aflr2.dat  |
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat).
|CSV file                           |surface_flow_pyCAPS_SU2_aflr2.csv  |

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat).
|Tecplot binary                     |flow_pyCAPS_SU2_aflr2.szplt        |

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat).
|Tecplot binary surface             |surface_flow_pyCAPS_SU2_aflr2.szplt|
Error in tecFileWriterClose: Not all node map values for zone 1 have been written.
Currently need 352 more values.0: Error finishing Tecplot file output.

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.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 Force - Pressure + Viscous
Cl =  0.650422 Cd =  0.030866
Cmz =  0.373254
Cx =  0.030866 Cy =  0.650422
Pressure Contribution
Cl_p =  0.650422 Cd_p =  0.030866
Cmz_p =  0.373254
Cx_p =  0.030866 Cy_p =  0.650422
Viscous Contribution
Cl_v =  0.0 Cd_v =  0.0
Cmz_v =  0.0
Cx_v =  0.0 Cy_v =  0.0

real	0m2.311s
user	0m1.621s
sys	0m0.286s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case su2_and_AFLR2_NodeDist_PyTest.py passed (as expected)
=================================================


=================================================
+ echo 'su2_and_AFLR2_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_and_AFLR2_PyTest.py test;
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
+ python -u su2_and_AFLR2_PyTest.py -outLevel=0
Saving geometry
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5

Getting mesh sizing parameters
	Mesh sizing name - 2DSlice
	Mesh sizing name - Airfoil
	Mesh sizing name - InFlow
	Mesh sizing name - OutFlow
	Mesh sizing name - TunnelWall
	Done getting mesh sizing parameters
Getting 2D mesh for body 1 (of 1)
 
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     Darwin 20.6.0 arm64
AFLR2    : Compile Date   06/13/22 @ 10:43AM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR2 IC : INPUT DATA CHECK
 
AFLR2 IC : Nodes, Faces      =       545         0
 
AFLR2    : CPU Time          =     0.000   seconds
 
AFLR2 EG : EDGE GRID RE-GENERATION
 
AFLR2 EG : Nodes, Edges      =       545       545
 
AFLR2    : CPU Time          =     0.000   seconds
 
AFLR2 IG : INITIAL GRID GENERATION
 
AFLR2 IG : Nodes, Faces      =         0         2
AFLR2 IG : Nodes, Faces      =       110       222
AFLR2 IG : Nodes, Faces      =       220       442
AFLR2 IG : Nodes, Faces      =       330       662
AFLR2 IG : Nodes, Faces      =       440       882
AFLR2 IG : Nodes, Faces      =       517      1036
AFLR2 IG : Nodes, Faces      =       545      1092
AFLR2 IG : Nodes, Faces      =       549      1092
AFLR2 IG : Nodes, Faces      =       545       545
 
AFLR2    : CPU Time          =     0.001   seconds
 
AFLR2 GG : FIELD GRID GENERATION
 
AFLR2 GGp: Nodes, Faces      =       545       545
AFLR2 GGp: Nodes, Faces      =      1083      1621
AFLR2 GGp: Nodes, Faces      =      1616      2687
AFLR2 GGp: Nodes, Faces      =      2144      3743
AFLR2 GGp: Nodes, Faces      =      2661      4777
AFLR2 GGp: Nodes, Faces      =      3171      5797
AFLR2 GGp: Nodes, Faces      =      3672      6799
AFLR2 GGp: Nodes, Faces      =      4158      7771
AFLR2 GGp: Nodes, Faces      =      4653      8761
AFLR2 GGp: Nodes, Faces      =      5142      9739
AFLR2 GGp: Nodes, Faces      =      5608     10671
AFLR2 GGp: Nodes, Faces      =      6055     11565
AFLR2 GGp: Nodes, Faces      =      6482     12419
AFLR2 GGp: Nodes, Faces      =      6880     13215
AFLR2 GGp: Nodes, Faces      =      7257     13969
AFLR2 GGp: Nodes, Faces      =      7614     14683
AFLR2 GGp: Nodes, Faces      =      7947     15349
AFLR2 GGp: Nodes, Faces      =      8276     16007
AFLR2 GGp: Nodes, Faces      =      8575     16605
AFLR2 GGp: Nodes, Faces      =      8869     17193
AFLR2 GGp: Nodes, Faces      =      9140     17735
AFLR2 GGp: Nodes, Faces      =      9401     18257
AFLR2 GGp: Nodes, Faces      =      9654     18763
AFLR2 GGp: Nodes, Faces      =      9887     19229
AFLR2 GGp: Nodes, Faces      =     10110     19675
AFLR2 GGp: Nodes, Faces      =     10315     20085
AFLR2 GGp: Nodes, Faces      =     10497     20449
AFLR2 GGp: Nodes, Faces      =     10656     20767
AFLR2 GGp: Nodes, Faces      =     10791     21037
AFLR2 GGp: Nodes, Faces      =     10919     21293
AFLR2 GGp: Nodes, Faces      =     11022     21499
AFLR2 GGp: Nodes, Faces      =     11092     21639
AFLR2 GGp: Nodes, Faces      =     11145     21745
AFLR2 GGp: Nodes, Faces      =     11156     21767
 
AFLR2    : CPU Time          =     0.047   seconds
 
AFLR2 QI : QUALITY IMPROVEMENT
 
AFLR2 QI : Nodes, Faces      =     11156     21767
AFLR2 QI : Nodes, Faces      =     11155       819
AFLR2 QI : Nodes, Faces      =     11155     10473
AFLR2 QI : Nodes, Faces      =     11155     21765
AFLR2 QI : Nodes, Faces      =     11154       863
AFLR2 QI : Nodes, Faces      =     11154     10450
AFLR2 QI : Nodes, Faces      =     11154     21763
AFLR2 QI : Nodes, Faces      =     11154      1031
AFLR2 QI : Nodes, Faces      =     11154     10366
AFLR2 QI : Nodes, Faces      =     11154     21763
AFLR2 QI : Nodes, Faces      =     11154      1637
AFLR2 QI : Nodes, Faces      =     11154     10063
AFLR2 QI : Nodes, Faces      =     11154     21763
AFLR2 QI : Nodes, Faces      =     11154      1025
AFLR2 QI : Nodes, Faces      =     11154     10369
AFLR2 QI : Nodes, Faces      =     11154     21763
AFLR2 QI : Nodes, Faces      =     11153      1013
AFLR2 QI : Nodes, Faces      =     11153     10374
AFLR2 QI : Nodes, Faces      =     11153      1013
AFLR2 QI : Nodes, Faces      =     11153     10374
 
AFLR2    : CPU Time          =     0.012   seconds
 
AFLR2    : DONE
Number of nodes = 11153
Number of elements = 11932
Number of tris = 1013
Number of quad = 10374

Writing TECPLOT file: pyCAPS_su2_aflr2.dat ....
Finished writing TECPLOT file


Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Airfoil
	Boundary condition name - InFlow
	Boundary condition name - OutFlow
	Boundary condition name - TunnelWall
	Warning: No boundary condition specified for capsGroup 2DSlice!
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "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: 0.4.
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 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_5.

Surface(s) plotted in the output file: BC_5, BC_2.
Input mesh file name: ../aflr2/aflr2.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: 10.
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_pyCAPS_su2_aflr2.dat.
Surface file name: surface_flow_pyCAPS_su2_aflr2.
Volume file name: flow_pyCAPS_su2_aflr2.
Restart file name: restart_flow_pyCAPS_su2_aflr2.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_5|
|                                   |                               BC_2|
+-----------------------------------------------------------------------+
|                     Inlet boundary|                               BC_4|
+-----------------------------------------------------------------------+
|                    Outlet boundary|                               BC_3|
+-----------------------------------------------------------------------+

-------------------- 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 ) -------------------
Two dimensional problem.
11153 grid points.
11485 volume elements.
3 surface markers.
24 boundary elements in index 0 (Marker = BC_3).
24 boundary elements in index 1 (Marker = BC_4).
399 boundary elements in index 2 (Marker = BC_5).
1013 triangles.
10472 quadrilaterals.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 1013 TRIANGLE volume elements.
There has been a re-orientation of 10424 QUADRILATERAL volume elements.
There has been a re-orientation of 447 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 1113.1.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 385.665. Mean K: 2.61256. Standard deviation K: 19.566.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        49.1197|             90|
|     CV Face Area Aspect Ratio|         1.0007|    2.05546e+32|
|           CV Sub-Volume Ratio|        1.00002|            inf|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     11153|    1/1.00|        10|
|         1|      2684|    1/4.16|   7.35846|
|         2|       539|    1/4.98|   4.94631|
+-------------------------------------------+
Finding max control volume width.
Wetted area = 2.06265 m.
Area projection in the x-plane = 0.211192 m, y-plane = 0.997011 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.102037 m.
Min. coordinate in the x-direction = 0.000323229 m, y-direction = -0.108492 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_5 is NOT a single straight.
Boundary marker BC_2 is a single straight.
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|        216054|             1|   m^2/s^2|        216054|
|            Velocity-X|       136.119|             1|       m/s|       136.119|
|            Velocity-Y|             0|             1|       m/s|             0|
|    Velocity Magnitude|       136.119|             1|       m/s|       136.119|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|           0.4|
+------------------------------------------------------------------------------+
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|  8.5845e-02|    1.513916|    4.384882|    4.363742|    6.989443|    0.166284|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  8.6180e-02|    1.946109|    4.322084|    4.705312|    7.456797|    0.325382|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  8.9261e-02|    2.257544|    4.616371|    5.007798|    7.715400|    1.470546|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  8.7495e-02|    2.349377|    4.662406|    5.105729|    7.801753|    8.047921|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  8.8792e-02|    2.417730|    4.698052|    5.187946|    7.883073|   -7.062004|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  9.0881e-02|    2.480421|    4.741759|    5.307157|    8.095858|   -2.936892|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  9.1398e-02|    2.524155|    4.786601|    5.404586|    8.153859|   -2.003993|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  9.0913e-02|    2.545934|    4.785549|    5.385153|    8.144449|   -1.503163|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  9.0721e-02|    2.573036|    4.904125|    5.462791|    8.248648|    4.944526|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  9.0853e-02|    2.577672|    5.051354|    5.532612|    8.405681| -202.444564|

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

Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       2.57767|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_pyCAPS_su2_aflr2.dat  |
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat).
|CSV file                           |surface_flow_pyCAPS_su2_aflr2.csv  |

Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat).
|Tecplot binary                     |flow_pyCAPS_su2_aflr2.szplt        |

Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat).
|Tecplot binary surface             |surface_flow_pyCAPS_su2_aflr2.szplt|
Error in tecFileWriterClose: Not all node map values for zone 1 have been written.
Currently need 798 more values.0: Error finishing Tecplot file output.

Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat).
Warning: there are 77 non-physical points in the solution.
Warning: 152 reconstructed states for upwinding are non-physical.

------------------------- 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 Force - Pressure + Viscous
Cl =  -1.299373 Cd =  0.006418
Cmz =  -0.555411
Cx =  0.006418 Cy =  -1.299373
Pressure Contribution
Cl_p =  -1.299373 Cd_p =  0.006418
Cmz_p =  -0.555411
Cx_p =  0.006418 Cy_p =  -1.299373
Viscous Contribution
Cl_v =  0.0 Cd_v =  0.0
Cmz_v =  0.0
Cx_v =  0.0 Cy_v =  0.0

real	0m2.816s
user	0m2.380s
sys	0m0.255s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case su2_and_AFLR2_PyTest.py passed (as expected)
=================================================


=================================================
+ echo 'su2_and_AFLR4_AFLR3_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_and_AFLR4_AFLR3_PyTest.py test;
+ python -u su2_and_AFLR4_AFLR3_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 4
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Wake, index = 3
	Name = Farfield, index = 4
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Wake, index = 3
	Name = Farfield, index = 4
AFLR4    : Proximity BG Surface Grid Generation Skipped
AFLR4    : No Modifications Required
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value

Writing TECPLOT file: AFLR4_Mesh_Surf_0.dat ....
Finished writing TECPLOT file


Writing TECPLOT file: AFLR4_Mesh_Surf_1.dat ....
Finished writing TECPLOT file


Writing TECPLOT file: AFLR4_Mesh_Surf_2.dat ....
Finished writing TECPLOT file


Writing TECPLOT file: AFLR4_Mesh_Surf_3.dat ....
Finished writing TECPLOT file

Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 4
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Wake, index = 3
	Name = Farfield, index = 4
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 4
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Wake, index = 3
	Name = Farfield, index = 4
Number of surface nodes - 6330
Number of surface elements - 12620
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     Darwin 20.6.0 arm64
AFLR2    : Compile Date   06/13/22 @ 10:43AM
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 10.22.22
AFLR4    : Version Date   06/24/22 @ 02:23PM
AFLR4    : Compile OS     Darwin 20.6.0 arm64
AFLR4    : Compile Date   06/24/22 @ 02:52PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.21
EGADS    : OpenCASCADE Version 7.4.1
EGADS    : ---------------------------------------

OVERALL  : CPU Time          =     0.468   seconds

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.21
EGADS    : OpenCASCADE Version 7.4.1
EGADS    : ---------------------------------------

OVERALL  : CPU Time          =     0.502   seconds
Volume mesh:
	Number of nodes = 39847
	Number of elements = 229886
	Number of triangles = 12620
	Number of quadrilatarals = 0
	Number of tetrahedrals = 217266
	Number of pyramids= 0
	Number of prisms= 0
	Number of hexahedrals= 0

Writing TECPLOT file: AFLR3_Mesh.dat ....
Finished writing TECPLOT file


Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Farfield
	Boundary condition name - Wake
	Boundary condition name - Wing1
	Boundary condition name - Wing2
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "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: 0.5901.
Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 50 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 15.8114 m.
Surface(s) where the force coefficients are evaluated and 
their reference origin for moment computation: 
   - BC_1 (0, 0, 0).
   - BC_2 (0, 0, 0) m.
Surface(s) plotted in the output file: BC_1, BC_2.
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: 10.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-8.
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|
|                 PARAVIEW|       250|
|         SURFACE_PARAVIEW|       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_su2AFLRTest.dat.
Surface file name: surface_flow_su2AFLRTest.
Volume file name: flow_su2AFLRTest.
Restart file name: restart_flow_su2AFLRTest.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_1|
|                                   |                               BC_2|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_4|
+-----------------------------------------------------------------------+
|                  Internal boundary|                               BC_3|
+-----------------------------------------------------------------------+

-------------------- 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.
39847 grid points.
217266 volume elements.
4 surface markers.
6726 boundary elements in index 0 (Marker = BC_1).
5418 boundary elements in index 1 (Marker = BC_2).
72 boundary elements in index 2 (Marker = BC_3).
404 boundary elements in index 3 (Marker = BC_4).
217266 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: 2.08442e+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: 4867.4. Mean K: 61.4053. Standard deviation K: 267.141.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        14.2892|        85.4113|
|     CV Face Area Aspect Ratio|        1.01233|         115950|
|           CV Sub-Volume Ratio|        1.03433|         876572|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     39847|    1/1.00|        10|
|         1|      6579|    1/6.06|   8.22898|
|         2|      1011|    1/6.51|   6.61152|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.90569 m.
Wetted area = 118.04 m^2.
Area projection in the x-plane = 11.156 m^2, y-plane = 4.97819 m^2, z-plane = 55.3972 m^2.
Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.582636 m.
Min. coordinate in the x-direction = 0 m, y-direction = -7.90569 m, z-direction = -0.41192 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Boundary marker BC_2 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|        226952|             1|   m^2/s^2|        226952|
|            Velocity-X|       200.779|             1|       m/s|       200.779|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|       3.50461|             1|       m/s|       3.50461|
|    Velocity Magnitude|       200.809|             1|       m/s|       200.809|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|        0.5901|
+------------------------------------------------------------------------------+
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|  1.1096e+00|   -0.070546|    2.291591|    2.031978|    5.420350|    1.973703|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  1.0564e+00|   -0.027742|    2.465488|    2.192011|    5.474209|    2.679463|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  1.0692e+00|    0.014684|    2.561802|    2.430686|    5.512716|    4.096693|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  1.0449e+00|   -0.028999|    2.595925|    2.569865|    5.458180|    6.037387|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.0346e+00|   -0.080764|    2.602330|    2.632331|    5.397765|    7.758173|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  1.0472e+00|   -0.096973|    2.604293|    2.657444|    5.390488|    8.978524|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  1.0605e+00|   -0.113236|    2.588879|    2.667397|    5.382320|    9.863146|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  1.0423e+00|   -0.157279|    2.531806|    2.674040|    5.334700|   10.390564|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  1.0541e+00|   -0.224359|    2.442078|    2.659383|    5.251687|   10.522400|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  1.0613e+00|   -0.276150|    2.386050|    2.617299|    5.195531|   10.312731|

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

Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -0.27615|          < -8|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_su2AFLRTest.dat       |
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|CSV file                           |surface_flow_su2AFLRTest.csv       |

Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview                           |flow_su2AFLRTest.vtu               |

Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview surface                   |surface_flow_su2AFLRTest.vtu       |

Writing the forces breakdown file (forces_breakdown_su2AFLRTest.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 Force - Pressure + Viscous
Cl =  0.79485 Cd =  0.077075
Cmx =  -0.001091 Cmy =  -0.203447 Cmz =  0.000115
Cx =  0.063191 Cy =  -8.7e-05 Cz =  0.796074
Pressure Contribution
Cl_p =  0.79485 Cd_p =  0.077075
Cmx_p =  -0.001091 Cmy_p =  -0.203447 Cmz_p =  0.000115
Cx_p =  0.063191 Cy_p =  -8.7e-05 Cz_p =  0.796074
Viscous Contribution
Cl_v =  0.0 Cd_v =  0.0
Cmx_v =  0.0 Cmy_v =  0.0 Cmz_v =  0.0
Cx_v =  0.0 Cy_v =  0.0 Cz_v =  0.0

real	0m53.906s
user	0m33.214s
sys	0m0.609s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case su2_and_AFLR4_AFLR3_PyTest.py passed (as expected)
=================================================

delaundo: /Users/jenkins/util/delaundo/delaundo/src/delaundo

=================================================
+ echo 'su2_and_Delaundo_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_and_Delaundo_PyTest.py test;
+ python -u su2_and_Delaundo_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5

Getting mesh sizing parameters
	Mesh sizing name - 2DSlice
	Mesh sizing name - Airfoil
	Mesh sizing name - InFlow
	Mesh sizing name - OutFlow
	Mesh sizing name - TunnelWall
	Done getting mesh sizing parameters
Getting edge discretization for body 1
	Delaundo expects 2D meshes be in the x-y plane... attempting to rotate mesh through node swapping!
	Swapping z and y coordinates!
Writing delaundo control file - delaundo.ctr
	Writing out *.pts file
Reading delaundo mesh file - delaundoMesh.mesh
	Swapping y and z coordinates!

Writing TECPLOT file: delaundoMesh.dat ....
Finished writing TECPLOT file


Writing SU2 file ....
SU2 expects 2D meshes be in the x-y plane... attempting to rotate mesh!
Swapping z and y coordinates!
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Airfoil
	Boundary condition name - InFlow
	Boundary condition name - OutFlow
	Boundary condition name - TunnelWall
	Warning: No boundary condition specified for capsGroup 2DSlice!
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "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: 0.4.
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 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_5.

Surface(s) plotted in the output file: BC_5, BC_2.
Input mesh file name: ../delaundo/delaundoMesh.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: 10.
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_delaundoMesh.dat.
Surface file name: surface_flow_delaundoMesh.
Volume file name: flow_delaundoMesh.
Restart file name: restart_flow_delaundoMesh.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_5|
|                                   |                               BC_2|
+-----------------------------------------------------------------------+
|                     Inlet boundary|                               BC_4|
+-----------------------------------------------------------------------+
|                    Outlet boundary|                               BC_3|
+-----------------------------------------------------------------------+

-------------------- 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 ) -------------------
Two dimensional problem.
6335 grid points.
12376 volume elements.
5 surface markers.
24 boundary elements in index 0 (Marker = BC_2).
24 boundary elements in index 1 (Marker = BC_3).
24 boundary elements in index 2 (Marker = BC_2).
24 boundary elements in index 3 (Marker = BC_4).
198 boundary elements in index 4 (Marker = BC_5).
12376 triangles.
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.
There has been a re-orientation of 294 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 999.917.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 1792.95. Mean K: 10.8141. Standard deviation K: 104.33.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        45.3524|        89.2457|
|     CV Face Area Aspect Ratio|        1.03245|        15.7098|
|           CV Sub-Volume Ratio|              1|        7.93642|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      6335|    1/1.00|        10|
|         1|      1815|    1/3.49|    8.0289|
|         2|       519|     1/3.5|    6.4401|
+-------------------------------------------+
Finding max control volume width.
Wetted area = 2.07206 m.
Area projection in the x-plane = 0.179342 m, y-plane = 1.00053 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.138492 m.
Min. coordinate in the x-direction = -0.00104577 m, y-direction = -0.0151891 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_5 is NOT a single straight.
Boundary marker BC_2 is a single straight.
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|        216054|             1|   m^2/s^2|        216054|
|            Velocity-X|       136.119|             1|       m/s|       136.119|
|            Velocity-Y|             0|             1|       m/s|             0|
|    Velocity Magnitude|       136.119|             1|       m/s|       136.119|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|           0.4|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

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

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

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

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  5.3019e-02|   -1.163686|    1.073255|    1.340929|    4.311650|    0.061671|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  5.5633e-02|   -1.568377|    0.814909|    0.963677|    3.916705|    0.144353|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  5.8206e-02|   -1.613815|    0.940123|    1.014538|    3.865902|    0.383098|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  5.6676e-02|   -1.678204|    0.986567|    1.029402|    3.782002|    0.970161|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  5.6715e-02|   -1.673240|    0.982512|    0.972025|    3.776795|    2.379908|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  5.7968e-02|   -1.632262|    0.968047|    0.868654|    3.827903|    6.320909|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  5.7892e-02|   -1.626018|    0.975724|    0.835054|    3.842259|   25.935722|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  5.9714e-02|   -1.650839|    1.000183|    0.890573|    3.818757|  -60.978870|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  5.9607e-02|   -1.679741|    1.014343|    0.938142|    3.785304|  -25.297357|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  6.0079e-02|   -1.692890|    1.005186|    0.937842|    3.767062|  -21.973132|

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

Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.69289|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_delaundoMesh.dat      |
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
|CSV file                           |surface_flow_delaundoMesh.csv      |

Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
|Tecplot binary                     |flow_delaundoMesh.szplt            |

Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
|Tecplot binary surface             |surface_flow_delaundoMesh.szplt    |
Error in tecFileWriterClose: Not all node map values for zone 1 have been written.
Currently need 492 more values.0: Error finishing Tecplot file output.

Writing the forces breakdown file (forces_breakdown_delaundoMesh.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 Force - Pressure + Viscous
Cl =  0.798939 Cd =  -0.03636
Cmz =  0.411603
Cx =  -0.03636 Cy =  0.798939
Pressure Contribution
Cl_p =  0.798939 Cd_p =  -0.03636
Cmz_p =  0.411603
Cx_p =  -0.03636 Cy_p =  0.798939
Viscous Contribution
Cl_v =  0.0 Cd_v =  0.0
Cmz_v =  0.0
Cx_v =  0.0 Cy_v =  0.0

real	0m1.830s
user	0m1.820s
sys	0m0.327s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case su2_and_Delaundo_PyTest.py passed (as expected)
=================================================


=================================================
+ echo 'su2_and_Tetgen_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_and_Tetgen_PyTest.py test;
+ python -u su2_and_Tetgen_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Farfield, index = 3
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Farfield, index = 3
Getting surface mesh for body 1 (of 3)
Getting surface mesh for body 2 (of 3)
Getting surface mesh for body 3 (of 3)
Body 1 (of 3)
Number of nodes    = 2236
Number of elements = 4468
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 4468
Number of quadrilateral elements = 0
Body 2 (of 3)
Number of nodes    = 636
Number of elements = 1268
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 1268
Number of quadrilateral elements = 0
Body 3 (of 3)
Number of nodes    = 265
Number of elements = 526
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 526
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3137
Total number of elements = 6262

Writing TECPLOT file: egadsTessMesh_Surf_0.dat ....
Finished writing TECPLOT file


Writing TECPLOT file: egadsTessMesh_Surf_1.dat ....
Finished writing TECPLOT file


Writing TECPLOT file: egadsTessMesh_Surf_2.dat ....
Finished writing TECPLOT file

Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 3
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Farfield, index = 3
Number of surface nodes - 3137
Number of surface elements - 6262
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000T1.00e-16
Delaunizing vertices...
Delaunay seconds:  0.046742
Creating surface mesh ...
Surface mesh seconds:  0.012311
Recovering boundaries...
Boundary recovery seconds:  0.151317
Removing exterior tetrahedra ...
Exterior tets removal seconds:  0.006106
Suppressing Steiner points ...
Steiner suppression seconds:  8e-06
Recovering Delaunayness...
Delaunay recovery seconds:  0.018262
Refining mesh...
  4186 insertions, added 2127 points, 136333 tetrahedra in queue.
  1393 insertions, added 422 points, 139726 tetrahedra in queue.
  1857 insertions, added 470 points, 137403 tetrahedra in queue.
  2476 insertions, added 427 points, 117743 tetrahedra in queue.
  3300 insertions, added 365 points, 61737 tetrahedra in queue.
  4399 insertions, added 357 points, 176 tetrahedra in queue.
  5864 insertions, added 617 points, 756 tetrahedra in queue.
Refinement seconds:  1.66696
Smoothing vertices...
Mesh smoothing seconds:  0.86781
Improving mesh...
Mesh improvement seconds:  0.041007
Jettisoning redundant points.

Writing nodes.
Writing elements.
Writing faces.
Writing edges.

Output seconds:  0.002165
Total running seconds:  2.81325

Statistics:

  Input points: 3137
  Input facets: 6262
  Input segments: 9393
  Input holes: 2
  Input regions: 0

  Mesh points: 7999
  Mesh tetrahedra: 39240
  Mesh faces: 81612
  Mesh faces on exterior boundary: 6264
  Mesh faces on input facets: 6264
  Mesh edges on input segments: 9394
  Steiner points on input segments:  1
  Steiner points inside domain: 4861

Done meshing using TetGen!
Volume mesher did not preserve surface elements - data transfer will NOT be possible.
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 - Wing1
	Boundary condition name - Wing2
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "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: 0.5901.
Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 50 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 15.8114 m.
Surface(s) where the force coefficients are evaluated and 
their reference origin for moment computation: 
   - BC_1 (0, 0, 0).
   - BC_2 (0, 0, 0) m.
Surface(s) plotted in the output file: BC_1, BC_2.
Input mesh file name: ../myMesh/tetgen_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|
|                 PARAVIEW|       250|
|         SURFACE_PARAVIEW|       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_pyCAPS_SU2_Tetgen.dat.
Surface file name: surface_flow_pyCAPS_SU2_Tetgen.
Volume file name: flow_pyCAPS_SU2_Tetgen.
Restart file name: restart_flow_pyCAPS_SU2_Tetgen.dat.

------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
|                        Marker Type|                        Marker Name|
+-----------------------------------------------------------------------+
|                         Euler wall|                               BC_1|
|                                   |                               BC_2|
+-----------------------------------------------------------------------+
|                          Far-field|                               BC_3|
+-----------------------------------------------------------------------+

-------------------- 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.
7999 grid points.
39240 volume elements.
3 surface markers.
4468 boundary elements in index 0 (Marker = BC_1).
1270 boundary elements in index 1 (Marker = BC_2).
526 boundary elements in index 2 (Marker = BC_3).
39240 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: 2.08926e+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: 414.134. Mean K: 30.5804. Standard deviation K: 37.5377.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        2.06191|        83.8135|
|     CV Face Area Aspect Ratio|        1.63355|         9085.8|
|           CV Sub-Volume Ratio|        1.03587|         479225|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      7999|    1/1.00|        10|
|         1|      1349|    1/5.93|   8.28737|
|         2|       230|    1/5.87|   6.89308|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.90569 m.
Wetted area = 120.046 m^2.
Area projection in the x-plane = 10.7914 m^2, y-plane = 4.58502 m^2, z-plane = 57.287 m^2.
Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.557773 m.
Min. coordinate in the x-direction = -0.00409054 m, y-direction = -7.90569 m, z-direction = -0.41192 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Boundary marker BC_2 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|        226952|             1|   m^2/s^2|        226952|
|            Velocity-X|       200.779|             1|       m/s|       200.779|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|       3.50461|             1|       m/s|       3.50461|
|    Velocity Magnitude|       200.809|             1|       m/s|       200.809|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|        0.5901|
+------------------------------------------------------------------------------+
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|  1.4234e-01|    0.620467|    3.052427|    2.095673|    6.111362|    1.788707|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  1.4558e-01|    0.796173|    3.294471|    3.082198|    6.298136|    2.133616|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  1.6634e-01|    0.720096|    3.417987|    3.326855|    6.235518|    3.142066|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  1.7053e-01|    0.655480|    3.386822|    3.349129|    6.144092|    4.533458|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.7343e-01|    0.665017|    3.326521|    3.274779|    6.140704|    5.702393|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      0.665017|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_pyCAPS_SU2_Tetgen.dat |
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
|CSV file                           |surface_flow_pyCAPS_SU2_Tetgen.csv |

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
|Paraview                           |flow_pyCAPS_SU2_Tetgen.vtu         |

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
|Paraview surface                   |surface_flow_pyCAPS_SU2_Tetgen.vtu |

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.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 Force - Pressure + Viscous
Cl =  0.741632 Cd =  0.130056
Cmx =  -0.004276 Cmy =  -0.208806 Cmz =  0.000954
Cx =  0.117093 Cy =  0.000346 Cz =  0.743789

real	0m12.520s
user	0m9.385s
sys	0m0.364s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case su2_and_Tetgen_PyTest.py passed (as expected)
=================================================


=================================================
+ echo 'su2_X43a_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_X43a_PyTest.py test;
+ python -u su2_X43a_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = x43A, index = 1
	Name = Farfield, index = 2
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 0
Getting surface mesh for body 1 (of 2)
Getting surface mesh for body 2 (of 2)
Body 1 (of 2)
Number of nodes    = 3817
Number of elements = 7634
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 7634
Number of quadrilateral elements = 0
Body 2 (of 2)
Number of nodes    = 5654
Number of elements = 11304
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 11304
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 9471
Total number of elements = 18938

Writing TECPLOT file: egadsTessMesh_Surf_0.dat ....
Finished writing TECPLOT file


Writing TECPLOT file: egadsTessMesh_Surf_1.dat ....
Finished writing TECPLOT file

Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = x43A, index = 1
	Name = Farfield, index = 2
Number of surface nodes - 9471
Number of surface elements - 18938
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000T1.00e-16
Delaunizing vertices...
Delaunay seconds:  0.13551
Creating surface mesh ...
Surface mesh seconds:  0.035072
Recovering boundaries...
Warning:  4 segments are not recovered.
Boundary recovery seconds:  0.405852
Removing exterior tetrahedra ...
Exterior tets removal seconds:  0.012359
Suppressing Steiner points ...
Steiner suppression seconds:  1.7e-05
Recovering Delaunayness...
Delaunay recovery seconds:  0.050705
Refining mesh...
  12628 insertions, added 5203 points, 17197 tetrahedra in queue.
Refinement seconds:  1.07897
Smoothing vertices...
Mesh smoothing seconds:  0.993146
Improving mesh...
Mesh improvement seconds:  0.090303
Jettisoning redundant points.

Writing nodes.
Writing elements.
Writing faces.
Writing edges.

Output seconds:  0.010963
Total running seconds:  2.81889

Statistics:

  Input points: 9471
  Input facets: 18938
  Input segments: 28407
  Input holes: 1
  Input regions: 0

  Mesh points: 14790
  Mesh tetrahedra: 60815
  Mesh faces: 131101
  Mesh faces on exterior boundary: 18942
  Mesh faces on input facets: 18942
  Mesh edges on input segments: 28409
  Steiner points on input segments:  2
  Steiner points inside domain: 5317

Done meshing using TetGen!
Volume mesher did not preserve surface elements - data transfer will NOT be possible.
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 - x43A
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.3.1) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.3.1 "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: 3.5.
Angle of attack (AoA): 3 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.

Surface(s) plotted in the output file: BC_1.
Input mesh file name: ../myMesh/tetgen_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|
|                 PARAVIEW|       250|
|         SURFACE_PARAVIEW|       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_x43a_Test.dat.
Surface file name: surface_flow_x43a_Test.
Volume file name: flow_x43a_Test.
Restart file name: restart_flow_x43a_Test.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.
14790 grid points.
60815 volume elements.
2 surface markers.
7638 boundary elements in index 0 (Marker = BC_1).
11304 boundary elements in index 1 (Marker = BC_2).
60815 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: 2.67744e+08.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 95.6599. Mean K: 0.525659. Standard deviation K: 2.58024.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        4.78299|        84.1311|
|     CV Face Area Aspect Ratio|        1.54669|        10300.5|
|           CV Sub-Volume Ratio|              1|    1.27098e+07|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     14790|    1/1.00|        10|
|         1|      2655|    1/5.57|   8.46168|
|         2|       473|    1/5.61|    7.1419|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 30 m.
Wetted area = 13597 m^2.
Area projection in the x-plane = 761.658 m^2, y-plane = 2062.86 m^2, z-plane = 5463.61 m^2.
Max. coordinate in the x-direction = 150 m, y-direction = 30 m, z-direction = 19 m.
Min. coordinate in the x-direction = 0 m, y-direction = -30 m, z-direction = -10.3 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|        916077|             1|   m^2/s^2|        916077|
|            Velocity-X|       1189.41|             1|       m/s|       1189.41|
|            Velocity-Y|             0|             1|       m/s|             0|
|            Velocity-Z|       62.3342|             1|       m/s|       62.3342|
|    Velocity Magnitude|       1191.04|             1|       m/s|       1191.04|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|           3.5|
+------------------------------------------------------------------------------+
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|  3.5464e-01|    2.732144|    5.666095|    4.729922|    8.731619|   -0.435726|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  3.9169e-01|    3.109260|    6.141815|    5.736603|    9.127013|   -0.165854|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  4.0133e-01|    3.307935|    6.378376|    5.793372|    9.273333|   -0.078779|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  4.0352e-01|    3.339444|    6.417048|    5.670682|    9.319457|   -0.068934|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  4.0194e-01|    3.227439|    6.286570|    5.565902|    9.203020|   -0.090107|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       3.22744|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_x43a_Test.dat         |
+-----------------------------------------------------------------------+

Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
|CSV file                           |surface_flow_x43a_Test.csv         |

Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
|Paraview                           |flow_x43a_Test.vtu                 |

Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
|Paraview surface                   |surface_flow_x43a_Test.vtu         |

Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
Warning: there are 118 non-physical points in the solution.
Warning: 519 reconstructed states for upwinding are non-physical.

------------------------- 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 Force - Pressure + Viscous
Cl =  -10.932638 Cd =  121.328891
Cmx =  26.600203 Cmy =  9831.532326 Cmz =  46.287092
Cx =  121.734784 Cy =  -0.091931 Cz =  -4.567792

real	0m17.395s
user	0m21.793s
sys	0m0.628s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case su2_X43a_PyTest.py passed (as expected)
=================================================

./execute_PyTestRegression.sh: line 403: ulimit: stack size: cannot modify limit: Operation not permitted
flowCart: /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//flowCart

=================================================
+ echo 'cart3d_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
cart3d_PyTest.py test;
+ python -u cart3d_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Loading AIM
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 7.674092
 Tessellating body 1 with  MaxEdge = 0.191852  Sag = 0.007674  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 9  > autoInputs.out
 Executing: ./aero.csh > aero.out
C_A  0.13578165
C_Y  -0.0022260526
C_N  0.0034959012
C_D  0.13582094
C_S  -0.0022260526
C_L  -0.0012449398
C_l  -0.00114789
C_m  -0.00654661
C_n  0.0353227
C_M_x  8.55497e-05
C_M_y  -0.00654661
C_M_z  0.0353412

real	0m18.572s
user	0m26.009s
sys	0m1.029s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case cart3d_PyTest.py passed (as expected)
=================================================


=================================================
+ echo 'cart3d_OpenMDAO_3_alpha_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
cart3d_OpenMDAO_3_alpha_PyTest.py test;
+ python -u cart3d_OpenMDAO_3_alpha_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1

Getting CFD design variables.......
	Number of design variables - 1
	Design Variable name - alpha
	Done getting CFD design variables
Getting CFD functional.......
	Number of design variables - 1
	Objective name - CL2
	Done getting CFD functional
 Body size = 10.084180
 Tessellating body 1 with  MaxEdge = 0.252104  Sag = 0.010084  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 5 -maxR 7  -mesh2d > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:04:45) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1
   (14:04:48) aero.csh done
 o case M0.5901A2B0_DP1, averaging data over 1 cycle(s)
alpha [2.]  CL2 [0.11325161]  CL 0.3365288
alpha [2.]  CL2 [0.11325161]  CL 0.3365288
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:04:49) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1
   (14:04:57) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               2188
              Estimated cutter memory:  0.000219 GB / DV
              Estimated xsensit memory: 0.004157 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (14:04:57) Linearizing cut-cells
   (14:04:57) ... done
   o Number of simultaneous xsensit jobs:  1
   (14:04:57) Computing gradients
   (14:05:01) ... done
 o case M0.5901A2B0_DP1, averaging data over 1 cycle(s)
CL2_alpha [[0.10892098]]
RUNNING THE L-BFGS-B CODE

           * * *

Machine precision = 2.220D-16
 N =            1     M =           10

At X0         0 variables are exactly at the bounds

At iterate    0    f=  1.13252D-01    |proj g|=  1.08921D-01
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:05:02) Running aero.csh on 2 core(s) in M0.5901A1.89108B0_DP1
   (14:05:08) aero.csh done
 o case M0.5901A1.89108B0_DP1, averaging data over 1 cycle(s)
alpha [1.89107902]  CL2 [0.1015741]  CL 0.31870681
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:05:09) Running aero.csh on 2 core(s) in M0.5901A1.89108B0_DP1
   (14:05:24) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               2188
              Estimated cutter memory:  0.000219 GB / DV
              Estimated xsensit memory: 0.004157 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (14:05:25) Linearizing cut-cells
   (14:05:25) ... done
   o Number of simultaneous xsensit jobs:  1
   (14:05:25) Computing gradients
   (14:05:29) ... done
 o case M0.5901A1.89108B0_DP1, averaging data over 1 cycle(s)
CL2_alpha [[0.10338203]]

At iterate    1    f=  1.01574D-01    |proj g|=  1.03382D-01
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:05:30) Running aero.csh on 2 core(s) in M0.5901A-0.141883B0_DP1
   (14:05:39) aero.csh done
 o case M0.5901A-0.141883B0_DP1, averaging data over 1 cycle(s)
alpha [-0.14188302]  CL2 [0.0002398]  CL -0.01530209
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:05:40) Running aero.csh on 2 core(s) in M0.5901A-0.141883B0_DP1
   (14:05:48) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               2188
              Estimated cutter memory:  0.000219 GB / DV
              Estimated xsensit memory: 0.004157 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (14:05:48) Linearizing cut-cells
   (14:05:48) ... done
   o Number of simultaneous xsensit jobs:  1
   (14:05:48) Computing gradients
   (14:05:52) ... done
 o case M0.5901A-0.141883B0_DP1, averaging data over 1 cycle(s)
CL2_alpha [[-0.00516383]]

At iterate    2    f=  2.39797D-04    |proj g|=  5.16383D-03
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:05:53) Running aero.csh on 2 core(s) in M0.5901A-0.0451693B0_DP1
   (14:05:58) aero.csh done
 o case M0.5901A-0.0451693B0_DP1, averaging data over 1 cycle(s)
alpha [-0.04516934]  CL2 [2.02152408e-06]  CL 0.00115329
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:05:59) Running aero.csh on 2 core(s) in M0.5901A-0.0451693B0_DP1
   (14:06:05) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               2188
              Estimated cutter memory:  0.000219 GB / DV
              Estimated xsensit memory: 0.004157 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (14:06:05) Linearizing cut-cells
   (14:06:05) ... done
   o Number of simultaneous xsensit jobs:  1
   (14:06:05) Computing gradients
   (14:06:09) ... done
 o case M0.5901A-0.0451693B0_DP1, averaging data over 1 cycle(s)
CL2_alpha [[0.00044919]]

At iterate    3    f=  2.02152D-06    |proj g|=  4.49187D-04
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:06:10) Running aero.csh on 2 core(s) in M0.5901A-0.0529089B0_DP1
   (14:06:14) aero.csh done
 o case M0.5901A-0.0529089B0_DP1, averaging data over 1 cycle(s)
alpha [-0.05290894]  CL2 [2.43246831e-08]  CL -0.00013421
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:06:15) Running aero.csh on 2 core(s) in M0.5901A-0.0529089B0_DP1
   (14:06:20) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               2188
              Estimated cutter memory:  0.000219 GB / DV
              Estimated xsensit memory: 0.004157 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (14:06:20) Linearizing cut-cells
   (14:06:20) ... done
   o Number of simultaneous xsensit jobs:  1
   (14:06:20) Computing gradients
   (14:06:24) ... done
 o case M0.5901A-0.0529089B0_DP1, averaging data over 1 cycle(s)
CL2_alpha [[3.23721877e-05]]

At iterate    4    f=  2.43247D-08    |proj g|=  3.23722D-05
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:06:25) Running aero.csh on 2 core(s) in M0.5901A-0.05351B0_DP1
   (14:06:30) aero.csh done
 o case M0.5901A-0.05351B0_DP1, averaging data over 1 cycle(s)
alpha [-0.05351004]  CL2 [3.32931733e-09]  CL -0.00023438
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:06:31) Running aero.csh on 2 core(s) in M0.5901A-0.05351B0_DP1
   (14:06:38) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               2188
              Estimated cutter memory:  0.000219 GB / DV
              Estimated xsensit memory: 0.004157 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (14:06:38) Linearizing cut-cells
   (14:06:38) ... done
   o Number of simultaneous xsensit jobs:  1
   (14:06:38) Computing gradients
   (14:06:42) ... done
 o case M0.5901A-0.05351B0_DP1, averaging data over 1 cycle(s)
CL2_alpha [[1.15017004e-07]]

At iterate    5    f=  3.32932D-09    |proj g|=  1.15017D-07

           * * *

Tit   = total number of iterations
Tnf   = total number of function evaluations
Tnint = total number of segments explored during Cauchy searches
Skip  = number of BFGS updates skipped
Nact  = number of active bounds at final generalized Cauchy point
Projg = norm of the final projected gradient
F     = final function value

           * * *

   N    Tit     Tnf  Tnint  Skip  Nact     Projg        F
    1      5      6      5     0     0   1.150D-07   3.329D-09
  F =   3.3293173290000004E-009

CONVERGENCE: NORM_OF_PROJECTED_GRADIENT_<=_PGTOL            
Optimization Complete
-----------------------------------
Optimized value: [-0.05351004]

real	2m4.407s
user	1m7.678s
sys	0m11.394s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case cart3d_OpenMDAO_3_alpha_PyTest.py passed (as expected)
=================================================


=================================================
+ echo 'cart3d_OpenMDAO_3_twist_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
cart3d_OpenMDAO_3_twist_PyTest.py test;
+ python -u cart3d_OpenMDAO_3_twist_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1

Getting CFD design variables.......
	Number of design variables - 1
	Design Variable name - twist
	Done getting CFD design variables
Getting CFD functional.......
	Number of design variables - 1
	Objective name - CL2
	Done getting CFD functional
 Body size = 10.084443
 Tessellating body 1 with  MaxEdge = 0.252111  Sag = 0.010084  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 5 -maxR 9  > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:06:45) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:06:58) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
twist [1. 2.]  CL2 [0.04586976]  CL -0.214172
twist [1. 2.]  CL2 [0.04586976]  CL -0.214172
 CAPS Info: Building sensitivity information for: twist[1,1]
 CAPS Info: Building sensitivity information for: twist[2,1]
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:06:59) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:07:34) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               21574
              Estimated cutter memory:  0.002157 GB / DV
              Estimated xsensit memory: 0.040991 GB / DV
              Available threads:        2
              # DVs:                    2
   o Number of simultaneous cutter jobs:   2
   (14:07:34) Linearizing cut-cells
   (14:07:36) ... done
   o Number of simultaneous xsensit jobs:  2
   (14:07:37) Computing gradients
              Adjusted OMP_NUM_THREADS to 1 for xsensit
   (14:07:41) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
CL2_twist [[0.02640792 0.02619742]]
RUNNING THE L-BFGS-B CODE

           * * *

Machine precision = 2.220D-16
 N =            2     M =           10

At X0         0 variables are exactly at the bounds

At iterate    0    f=  4.58698D-02    |proj g|=  2.64079D-02
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 10.084443
 Tessellating body 1 with  MaxEdge = 0.252111  Sag = 0.010084  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 5 -maxR 9  > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:07:42) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:08:07) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
twist [0.97359208 1.97380258]  CL2 [0.04430268]  CL -0.210482
 CAPS Info: Building sensitivity information for: twist[1,1]
 CAPS Info: Building sensitivity information for: twist[2,1]
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:08:08) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:08:39) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               21574
              Estimated cutter memory:  0.002157 GB / DV
              Estimated xsensit memory: 0.040991 GB / DV
              Available threads:        2
              # DVs:                    2
   o Number of simultaneous cutter jobs:   2
   (14:08:40) Linearizing cut-cells
   (14:08:42) ... done
   o Number of simultaneous xsensit jobs:  2
   (14:08:42) Computing gradients
              Adjusted OMP_NUM_THREADS to 1 for xsensit
   (14:08:46) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
CL2_twist [[0.02595604 0.02574775]]

At iterate    1    f=  4.43027D-02    |proj g|=  2.59560D-02
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 10.084437
 Tessellating body 1 with  MaxEdge = 0.252111  Sag = 0.010084  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 5 -maxR 9  > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:08:47) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:08:56) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
twist [-0.54327004  0.4737495 ]  CL2 [0.00011341]  CL 0.0106492
 CAPS Info: Building sensitivity information for: twist[1,1]
 CAPS Info: Building sensitivity information for: twist[2,1]
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:08:57) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:09:32) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               21574
              Estimated cutter memory:  0.002157 GB / DV
              Estimated xsensit memory: 0.040991 GB / DV
              Available threads:        2
              # DVs:                    2
   o Number of simultaneous cutter jobs:   2
   (14:09:32) Linearizing cut-cells
   (14:09:34) ... done
   o Number of simultaneous xsensit jobs:  2
   (14:09:34) Computing gradients
              Adjusted OMP_NUM_THREADS to 1 for xsensit
   (14:09:39) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
CL2_twist [[-0.00132498 -0.00131139]]

At iterate    2    f=  1.13406D-04    |proj g|=  1.32498D-03
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 10.084437
 Tessellating body 1 with  MaxEdge = 0.252111  Sag = 0.010084  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 5 -maxR 9  > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:09:40) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:09:49) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
twist [-0.4695991   0.54644784]  CL2 [9.69399622e-07]  CL -0.00098458
 CAPS Info: Building sensitivity information for: twist[1,1]
 CAPS Info: Building sensitivity information for: twist[2,1]
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:09:50) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:10:12) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               21574
              Estimated cutter memory:  0.002157 GB / DV
              Estimated xsensit memory: 0.040991 GB / DV
              Available threads:        2
              # DVs:                    2
   o Number of simultaneous cutter jobs:   2
   (14:10:12) Linearizing cut-cells
   (14:10:14) ... done
   o Number of simultaneous xsensit jobs:  2
   (14:10:14) Computing gradients
              Adjusted OMP_NUM_THREADS to 1 for xsensit
   (14:10:18) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
CL2_twist [[0.00012252 0.00012118]]

At iterate    3    f=  9.69400D-07    |proj g|=  1.22516D-04
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 10.084437
 Tessellating body 1 with  MaxEdge = 0.252111  Sag = 0.010084  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 5 -maxR 9  > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:10:20) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:10:40) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
twist [-0.47583461  0.54029853]  CL2 [1.35059249e-09]  CL 3.675e-05
 CAPS Info: Building sensitivity information for: twist[1,1]
 CAPS Info: Building sensitivity information for: twist[2,1]
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (14:10:41) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (14:11:23) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               21574
              Estimated cutter memory:  0.002157 GB / DV
              Estimated xsensit memory: 0.040991 GB / DV
              Available threads:        2
              # DVs:                    2
   o Number of simultaneous cutter jobs:   2
   (14:11:23) Linearizing cut-cells
   (14:11:25) ... done
   o Number of simultaneous xsensit jobs:  2
   (14:11:25) Computing gradients
              Adjusted OMP_NUM_THREADS to 1 for xsensit
   (14:11:29) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
CL2_twist [[-4.57244740e-06 -4.52300798e-06]]

At iterate    4    f=  1.35059D-09    |proj g|=  4.57245D-06

           * * *

Tit   = total number of iterations
Tnf   = total number of function evaluations
Tnint = total number of segments explored during Cauchy searches
Skip  = number of BFGS updates skipped
Nact  = number of active bounds at final generalized Cauchy point
Projg = norm of the final projected gradient
F     = final function value

           * * *

   N    Tit     Tnf  Tnint  Skip  Nact     Projg        F
    2      4      5      4     0     0   4.572D-06   1.351D-09
  F =   1.3505924857000001E-009

CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH             
Optimization Complete
-----------------------------------
Optimized values: [-0.47583461  0.54029853]

real	4m47.627s
user	4m0.487s
sys	0m15.031s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case cart3d_OpenMDAO_3_twist_PyTest.py passed (as expected)
=================================================


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

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

Fun3D
=================================================

All tests pass!


=================================================
=================================================
[GNU C Compiler (gcc)] Sleeping for 5 seconds due to JENKINS-32191...
[GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining
[Clang] Sleeping for 5 seconds due to JENKINS-32191...
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1')
[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/CFD,DARWINM1,viggen)
[Static Analysis] Using reference build 'ESP_UndefinedCaps/CASREV=7.4,ESPTEST=CAPS/CFD,ESP_ARCH=DARWINM1,buildnode=viggen #161' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1
[Static Analysis] -> All quality gates have been passed
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_UndefinedCaps/CASREV=7.4,ESPTEST=CAPS/CFD,ESP_ARCH=DARWINM1,buildnode=viggen #162'.
[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