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Skipping 548 KB.. Full Log
	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    = 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 3)
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
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    = 16014
Total number of elements = 32016
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 - 16014, elements - 32016
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds:  0.370525
Creating surface mesh ...
Surface mesh seconds:  0.045047
Recovering boundaries...
Boundary recovery seconds:  0.212568
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds:  0.088973
Recovering Delaunayness...
Delaunay recovery seconds:  0.109296
Refining mesh...
  21346 insertions, added 17000 points, 773281 tetrahedra in queue.
  7108 insertions, added 2714 points, 325605 tetrahedra in queue.
Refinement seconds:  3.04565
Smoothing vertices...
Mesh smoothing seconds:  4.02608
Improving mesh...
Mesh improvement seconds:  0.129015

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

Output seconds:  0.026853
Total running seconds:  8.05481

Statistics:

  Input points: 16014
  Input facets: 32016
  Input segments: 48024
  Input holes: 2
  Input regions: 0

  Mesh points: 37066
  Mesh tetrahedra: 178778
  Mesh faces: 373564
  Mesh faces on exterior boundary: 32016
  Mesh faces on input facets: 32016
  Mesh edges on input segments: 48024
  Steiner points inside domain: 21052

Done meshing using TetGen!
Getting CFD boundary conditions
	Boundary condition name - Wing1
	Boundary condition name - Wing2
	Boundary condition name - Farfield
	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	0m16.654s
user	0m17.633s
sys	0m0.311s
+ status=0
+ set +x

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

=================================================
Summary of examples NOT finished as expected

./fun3dAFLR2Test

See cCAPSlog.txt for more details.
=================================================

=================================================
=================================================
++ true
++ '[' '!' -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 = 4
	Name = TunnelWall, index = 1
	Name = OutFlow, index = 2
	Name = InFlow, index = 3
	Name = Airfoil, index = 4

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          =     0.008   seconds
 
AFLR2 QI : QUALITY IMPROVEMENT
 
AFLR2 QI : Nodes, Faces      =      3715      7206
 
AFLR2    : CPU Time          =     0.001   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          =     0.003   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
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.4.0 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.4.
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_4.

Surface(s) plotted in the output file: BC_4, BC_1.
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_4|
|                                   |                               BC_1|
+-----------------------------------------------------------------------+
|                     Inlet boundary|                               BC_3|
+-----------------------------------------------------------------------+
|                    Outlet boundary|                               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 ) -------------------
Two dimensional problem.
3715 grid points.
7304 volume elements.
3 surface markers.
24 boundary elements in index 0 (Marker = BC_2).
24 boundary elements in index 1 (Marker = BC_3).
78 boundary elements in index 2 (Marker = BC_4).
7304 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 7239 TRIANGLE volume elements.
There has been a re-orientation of 126 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 1045.19.
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: 3.41831. Standard deviation K: 17.2669.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        47.6942|        89.9998|
|     CV Face Area Aspect Ratio|              1|    7.22422e+32|
|           CV Sub-Volume Ratio|              1|            inf|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      3715|    1/1.00|        10|
|         1|      1095|    1/3.39|   8.14365|
|         2|       302|    1/3.63|   6.41515|
+-------------------------------------------+
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_4 is NOT a single straight.
Boundary marker BC_1 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|  3.4368e-02|    1.664872|    4.536314|    4.601854|    7.140693|    0.653926|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  3.4457e-02|    2.058705|    4.517980|    4.868364|    7.519912|   11.025945|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  3.4709e-02|    2.163236|    4.628188|    4.984140|    7.649448|   -3.811426|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  3.8413e-02|    2.319741|    4.695154|    5.097248|    7.817586|   -3.017393|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  3.8642e-02|    2.484688|    4.998683|    5.167356|    7.862247|   -1.389523|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  3.8508e-02|    2.345870|    4.936228|    5.118909|    7.927958|    5.763541|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  3.7695e-02|    2.363077|    4.865608|    5.184619|    7.975405|    8.191119|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  3.7385e-02|    2.481188|    5.105954|    5.174877|    8.021927|   17.968608|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  3.7587e-02|    2.534681|    5.086258|    5.277675|    8.214142| 1493.845510|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  3.8946e-02|    2.555210|    4.974457|    5.260351|    8.078045|    8.171518|

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

Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       2.55521|         < -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 156 more values.0: Error finishing Tecplot file output.

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat).
+-----------------------------------------------------------------------+
Warning: there are 62 non-physical points in the solution.
Warning: 57 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 =  -0.533651 Cd =  -0.065306
Cmz =  -0.36014
Cx =  -0.065306 Cy =  -0.533651
Pressure Contribution
Cl_p =  -0.533651 Cd_p =  -0.065306
Cmz_p =  -0.36014
Cx_p =  -0.065306 Cy_p =  -0.533651
Viscous Contribution
Cl_v =  0.0 Cd_v =  0.0
Cmz_v =  0.0
Cx_v =  0.0 Cy_v =  0.0

real	0m2.733s
user	0m1.745s
sys	0m0.465s
+ 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;
+ python -u su2_and_AFLR2_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
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 = 4
	Name = TunnelWall, index = 1
	Name = OutFlow, index = 2
	Name = InFlow, index = 3
	Name = Airfoil, index = 4

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          =     0.028   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          =     0.017   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
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.4.0 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.4.
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_4.

Surface(s) plotted in the output file: BC_4, BC_1.
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_4|
|                                   |                               BC_1|
+-----------------------------------------------------------------------+
|                     Inlet boundary|                               BC_3|
+-----------------------------------------------------------------------+
|                    Outlet boundary|                               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 ) -------------------
Two dimensional problem.
11153 grid points.
11509 volume elements.
2 surface markers.
24 boundary elements in index 0 (Marker = BC_3).
399 boundary elements in index 1 (Marker = BC_4).
1111 triangles.
10398 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 1047 TRIANGLE volume elements.
There has been a re-orientation of 10386 QUADRILATERAL volume elements.
There has been a re-orientation of 423 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 1028.64.
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: 2.7666. Standard deviation K: 20.124.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        1.95707|             90|
|     CV Face Area Aspect Ratio|        1.00061|    9.87385e+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|      2679|    1/4.16|    7.3516|
|         2|       536|       1/5|   4.93252|
+-------------------------------------------+
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_4 is NOT a single straight.
Boundary marker BC_1 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|  1.1249e-01|    1.363230|    4.233693|    4.451202|    6.838948|    0.202010|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  9.9750e-02|    2.030846|    4.561806|    4.739835|    7.532881|    0.570988|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  9.6787e-02|    2.207276|    4.710208|    4.952430|    7.645285|    1.646106|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  9.2517e-02|    2.329056|    4.790032|    5.021583|    7.717711|    5.610446|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  9.4617e-02|    2.357227|    4.859355|    5.084955|    7.789650|   -4.926794|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  9.5432e-02|    2.363428|    4.787753|    5.111169|    7.829491|   -3.415938|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  9.6612e-02|    2.377774|    4.731973|    5.143980|    7.848642|   -1.430681|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  9.8356e-02|    2.366322|    4.936388|    5.204019|    7.828277|   -1.849824|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  1.0000e-01|    2.317889|    4.763150|    5.101914|    7.895163|   -1.698246|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  9.8463e-02|    2.454616|    5.000278|    5.305493|    7.969875|   -1.208344|

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

Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       2.45462|         < -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 132 non-physical points in the solution.
Warning: 46 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 =  -0.358335 Cd =  0.296551
Cmz =  -0.044686
Cx =  0.296551 Cy =  -0.358335
Pressure Contribution
Cl_p =  -0.358335 Cd_p =  0.296551
Cmz_p =  -0.044686
Cx_p =  0.296551 Cy_p =  -0.358335
Viscous Contribution
Cl_v =  0.0 Cd_v =  0.0
Cmz_v =  0.0
Cx_v =  0.0 Cy_v =  0.0

real	0m4.463s
user	0m2.438s
sys	0m0.293s
+ 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 10.22.23
AFLR4    : Version Date   07/14/22 @ 02:23PM
AFLR4    : Compile OS     Darwin 20.6.0 arm64
AFLR4    : Compile Date   07/19/22 @ 12:00AM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

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

OVERALL  : CPU Time          =     0.264   seconds

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

OVERALL  : CPU Time          =     0.482   seconds
Volume mesh:
	Number of nodes = 38826
	Number of elements = 223750
	Number of triangles = 12620
	Number of quadrilatarals = 0
	Number of tetrahedrals = 211130
	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 (7.4.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.4.0 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.5901.
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.
38826 grid points.
211130 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).
211130 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.)|        14.0925|        85.9518|
|     CV Face Area Aspect Ratio|        1.14005|        60867.7|
|           CV Sub-Volume Ratio|        1.03726|         607347|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     38826|    1/1.00|        10|
|         1|      6383|    1/6.08|   8.21723|
|         2|      1000|    1/6.38|   6.64469|
+-------------------------------------------+
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|  1.1005e+00|   -0.064909|    2.297228|    2.037614|    5.425986|    1.970617|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  1.0458e+00|   -0.014516|    2.466362|    2.223565|    5.483880|    2.678366|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  1.0443e+00|    0.022914|    2.554907|    2.443241|    5.515945|    4.099409|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  9.9973e-01|   -0.019174|    2.593253|    2.572829|    5.462315|    6.015263|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.0099e+00|   -0.059747|    2.606655|    2.628999|    5.413180|    7.694135|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  1.0053e+00|   -0.071391|    2.612654|    2.644047|    5.409498|    8.897028|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  9.8030e-01|   -0.078187|    2.607698|    2.653207|    5.412129|    9.757654|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  9.7162e-01|   -0.103592|    2.575126|    2.666094|    5.385661|   10.244649|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  9.8577e-01|   -0.151764|    2.516933|    2.669582|    5.327676|   10.338258|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  1.0020e+00|   -0.201185|    2.455402|    2.646642|    5.273673|   10.144963|

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

Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.201185|          < -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 =  0.797006 Cd =  0.078562
Cmx =  -0.000385 Cmy =  -0.203388 Cmz =  5e-05
Cx =  0.06464 Cy =  -7.7e-05 Cz =  0.798256
Pressure Contribution
Cl_p =  0.797006 Cd_p =  0.078562
Cmx_p =  -0.000385 Cmy_p =  -0.203388 Cmz_p =  5e-05
Cx_p =  0.06464 Cy_p =  -7.7e-05 Cz_p =  0.798256
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	0m53.972s
user	0m29.418s
sys	0m0.712s
+ 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 (7.4.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.4.0 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.4.
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|  5.4221e-02|   -1.163686|    1.073255|    1.340929|    4.311650|    0.061671|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  5.7282e-02|   -1.568377|    0.814909|    0.963677|    3.916705|    0.144353|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  5.5018e-02|   -1.613815|    0.940123|    1.014538|    3.865902|    0.383098|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  5.4744e-02|   -1.678204|    0.986567|    1.029402|    3.782002|    0.970161|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  5.7776e-02|   -1.673240|    0.982512|    0.972025|    3.776795|    2.379908|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  5.8758e-02|   -1.632262|    0.968047|    0.868654|    3.827903|    6.320909|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  6.0704e-02|   -1.626018|    0.975724|    0.835054|    3.842259|   25.935722|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  6.0494e-02|   -1.650839|    1.000183|    0.890573|    3.818757|  -60.978870|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  6.1277e-02|   -1.679741|    1.014343|    0.938142|    3.785304|  -25.297357|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  6.4255e-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	0m1.837s
user	0m1.809s
sys	0m0.322s
+ 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, elements - 6262
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds:  0.066577
Creating surface mesh ...
Surface mesh seconds:  0.013327
Recovering boundaries...
Boundary recovery seconds:  0.142
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds:  0.012777
Suppressing Steiner points ...
Steiner suppression seconds:  6e-06
Recovering Delaunayness...
Delaunay recovery seconds:  0.0195
Refining mesh...
  4186 insertions, added 2159 points, 126369 tetrahedra in queue.
  1393 insertions, added 415 points, 129993 tetrahedra in queue.
  1857 insertions, added 443 points, 128610 tetrahedra in queue.
  2476 insertions, added 560 points, 116391 tetrahedra in queue.
  3300 insertions, added 523 points, 73871 tetrahedra in queue.
  4399 insertions, added 397 points, 746 tetrahedra in queue.
Refinement seconds:  1.21576
Smoothing vertices...
Mesh smoothing seconds:  0.897918
Improving mesh...
Mesh improvement seconds:  0.037578
Jettisoning redundant points.

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

Output seconds:  0.006126
Total running seconds:  2.41205

Statistics:

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

  Mesh points: 8158
  Mesh tetrahedra: 40383
  Mesh faces: 83898
  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: 5020

Done meshing using TetGen!
Volume mesher did not preserve surface elements - data transfer will NOT be possible.

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 (7.4.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.4.0 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.5901.
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.
8158 grid points.
40383 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).
40383 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.)|        1.92303|        83.9055|
|     CV Face Area Aspect Ratio|        1.55295|        3521.13|
|           CV Sub-Volume Ratio|        1.01617|         206050|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      8158|    1/1.00|        10|
|         1|      1352|    1/6.03|   8.23927|
|         2|       218|     1/6.2|   6.72677|
+-------------------------------------------+
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|  1.9002e-01|    0.616193|    3.048153|    2.091399|    6.107088|    1.805051|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  1.8758e-01|    0.775229|    3.247319|    3.001437|    6.275319|    2.174893|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  1.9039e-01|    0.702974|    3.288113|    3.247932|    6.198943|    3.210083|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  1.9531e-01|    0.601014|    3.220958|    3.293492|    6.064222|    4.596839|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.9800e-01|    0.593648|    3.197132|    3.233731|    6.058200|    5.787584|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      0.593648|         < -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 =  0.759974 Cd =  0.131311
Cmx =  -0.003194 Cmy =  -0.212257 Cmz =  0.000553
Cx =  0.118028 Cy =  0.000335 Cz =  0.76215

real	0m7.729s
user	0m7.088s
sys	0m0.365s
+ 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, elements - 18938
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds:  0.127114
Creating surface mesh ...
Surface mesh seconds:  0.02329
Recovering boundaries...
Warning:  4 segments are not recovered.
Boundary recovery seconds:  0.282752
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds:  0.025492
Suppressing Steiner points ...
Steiner suppression seconds:  1.9e-05
Recovering Delaunayness...
Delaunay recovery seconds:  0.038563
Refining mesh...
  12628 insertions, added 5171 points, 10497 tetrahedra in queue.
Refinement seconds:  1.09292
Smoothing vertices...
Mesh smoothing seconds:  1.15459
Improving mesh...
Mesh improvement seconds:  0.055777
Jettisoning redundant points.

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

Output seconds:  0.011435
Total running seconds:  2.82557

Statistics:

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

  Mesh points: 14824
  Mesh tetrahedra: 61034
  Mesh faces: 131539
  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: 5351

Done meshing using TetGen!
Volume mesher did not preserve surface elements - data transfer will NOT be possible.

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 (7.4.0) "


Running SU2......

-------------------------------------------------------------------------
|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 7.4.0 "Blackbird"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io                        |
|                                                                       |
| The SU2 Project is maintained by the SU2 Foundation                   |
| (http://su2foundation.org)                                            |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors                                 |
|                                                                       |
| SU2 is free software; you can redistribute it and/or                  |
| modify it under the terms of the GNU Lesser General Public            |
| License as published by the Free Software Foundation; either          |
| version 2.1 of the License, or (at your option) any later version.    |
|                                                                       |
| SU2 is distributed in the hope that it will be useful,                |
| but WITHOUT ANY WARRANTY; without even the implied warranty of        |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU      |
| Lesser General Public License for more details.                       |
|                                                                       |
| You should have received a copy of the GNU Lesser General Public      |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>.   |
-------------------------------------------------------------------------

Parsing config file for zone 0

----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 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.
14824 grid points.
61034 volume elements.
2 surface markers.
7638 boundary elements in index 0 (Marker = BC_1).
11304 boundary elements in index 1 (Marker = BC_2).
61034 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.)|       0.041314|        83.9178|
|     CV Face Area Aspect Ratio|        1.62826|        13202.4|
|           CV Sub-Volume Ratio|              1|    1.24042e+07|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     14824|    1/1.00|        10|
|         1|      2668|    1/5.56|   8.46899|
|         2|       492|    1/5.42|   7.23073|
+-------------------------------------------+
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|  3.9070e-01|    2.731645|    5.665596|    4.729423|    8.731121|   -0.374100|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  3.7385e-01|    3.120118|    6.139645|    5.659982|    9.120238|   -0.138499|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  3.5074e-01|    3.198604|    6.246170|    5.767210|    9.165358|   -0.054805|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  3.4969e-01|    3.243196|    6.288748|    5.704421|    9.196215|   -0.048476|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  3.4892e-01|    3.234245|    6.291775|    5.521178|    9.205466|   -0.072036|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       3.23424|         < -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 131 non-physical points in the solution.
Warning: 63 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 =  -8.581041 Cd =  119.121674
Cmx =  -19.065106 Cmy =  9458.970655 Cmz =  200.291547
Cx =  119.407518 Cy =  2.431409 Cz =  -2.334934

real	0m27.268s
user	0m20.699s
sys	0m0.659s
+ 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 = 3.796888
 Tessellating body 1 with  MaxEdge = 0.094922  Sag = 0.003797  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 9  > autoInputs.out
 Executing: ./aero.csh > aero.out
C_A  0.050108722
C_Y  -0.0015626888
C_N  0.0065057683
C_D  0.050305245
C_S  -0.0015626888
C_L  0.0047530359
C_l  0.00381162
C_m  -0.00346146
C_n  -0.0401149
C_M_x  0.00240931
C_M_y  -0.00346146
C_M_z  -0.0402235

real	0m44.112s
user	0m36.288s
sys	0m1.704s
+ 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
----------------------------------------
>>> alpha [2.]
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 = 3.625615
 Tessellating body 1 with  MaxEdge = 0.090640  Sag = 0.003626  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
   (11:03:05) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1
   (11:03:11) aero.csh done
 o case M0.5901A2B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.01631562]  CL 0.12773309
----------------------------------------
----------------------------------------
>>> alpha [2.]
>>> CL2 [0.01631562]  CL 0.12773309
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:03:12) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1
   (11:03:26) 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
   (11:03:26) Linearizing cut-cells
   (11:03:26) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:03:26) Computing gradients
   (11:03:30) ... done
 o case M0.5901A2B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[0.01572627]]
========================================
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=  1.63156D-02    |proj g|=  1.57263D-02
----------------------------------------
>>> alpha [1.98427373]
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:03:32) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1
   (11:03:46) aero.csh done
 o case M0.5901A1.98427B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.01606724]  CL 0.12675617
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:03:48) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1
   (11:03:56) 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
   (11:03:56) Linearizing cut-cells
   (11:03:56) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:03:56) Computing gradients
   (11:04:01) ... done
 o case M0.5901A1.98427B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[0.01560329]]
========================================

At iterate    1    f=  1.60672D-02    |proj g|=  1.56033D-02
----------------------------------------
>>> alpha [-0.01099175]
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:04:01) Running aero.csh on 2 core(s) in M0.5901A-0.0109917B0_DP1
   (11:04:07) aero.csh done
 o case M0.5901A-0.0109917B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [6.05653711e-06]  CL 0.00246101
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:04:08) Running aero.csh on 2 core(s) in M0.5901A-0.0109917B0_DP1
   (11:04:16) 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
   (11:04:16) Linearizing cut-cells
   (11:04:16) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:04:16) Computing gradients
   (11:04:20) ... done
 o case M0.5901A-0.0109917B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[0.00031042]]
========================================

At iterate    2    f=  6.05654D-06    |proj g|=  3.10424D-04
----------------------------------------
>>> alpha [-0.05149286]
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:04:21) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1
   (11:04:35) aero.csh done
 o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [2.59817062e-10]  CL 1.612e-05
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:04:36) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1
   (11:04:44) 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
   (11:04:45) Linearizing cut-cells
   (11:04:45) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:04:45) Computing gradients
   (11:04:49) ... done
 o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[2.03612433e-06]]
========================================

At iterate    3    f=  2.59817D-10    |proj g|=  2.03612D-06
----------------------------------------
>>> alpha [-0.05176027]
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:04:50) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1
   (11:04:57) aero.csh done
 o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [9.25766089e-15]  CL 1e-07
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:04:58) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1
   (11:05:08) 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
   (11:05:09) Linearizing cut-cells
   (11:05:09) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:05:09) Computing gradients
   (11:05:13) ... done
 o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[1.21372408e-08]]
========================================

At iterate    4    f=  9.25766D-15    |proj g|=  1.21372D-08

           * * *

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      4      5      4     0     0   1.214D-08   9.258D-15
  F =   9.2576608860000000E-015

CONVERGENCE: NORM_OF_PROJECTED_GRADIENT_<=_PGTOL            
Optimization Complete
-----------------------------------
Optimized value: [-0.05176027]

real	2m17.856s
user	1m4.971s
sys	0m10.856s
+ 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;
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
+ python -u cart3d_OpenMDAO_3_twist_PyTest.py -outLevel=0
----------------------------------------
>>> twist [4.]
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 = 3.630958
 Tessellating body 1 with  MaxEdge = 0.018155  Sag = 0.000908  Angle = 10.000000
 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7  -symmY -halfBody > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:05:20) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:06:22) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.00411365]  CL 0.0641354
----------------------------------------
----------------------------------------
>>> twist [4.]
>>> CL2 [0.00411365]  CL 0.0641354
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:06:25) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:07:08) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               37528
              Estimated cutter memory:  0.003753 GB / DV
              Estimated xsensit memory: 0.071303 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (11:07:08) Linearizing cut-cells
   (11:07:10) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:07:11) Computing gradients
   (11:07:15) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[0.00209614]]
========================================
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=  4.11365D-03    |proj g|=  2.09614D-03
----------------------------------------
>>> twist [3.99790386]
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 3.630955
 Tessellating body 1 with  MaxEdge = 0.018155  Sag = 0.000908  Angle = 10.000000
 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7  -symmY -halfBody > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:07:19) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:08:00) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.00411103]  CL 0.0641104
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:08:03) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:09:20) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               37527
              Estimated cutter memory:  0.003753 GB / DV
              Estimated xsensit memory: 0.071301 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (11:09:20) Linearizing cut-cells
   (11:09:22) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:09:22) Computing gradients
   (11:09:26) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[0.00209539]]
========================================

At iterate    1    f=  4.11103D-03    |proj g|=  2.09539D-03
----------------------------------------
>>> twist [-1.80569538]
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 3.627699
 Tessellating body 1 with  MaxEdge = 0.018138  Sag = 0.000907  Angle = 10.000000
 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7  -symmY -halfBody > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:09:31) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:10:04) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.00077483]  CL -0.027831
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:10:07) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:11:06) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               37739
              Estimated cutter memory:  0.003774 GB / DV
              Estimated xsensit memory: 0.071704 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (11:11:06) Linearizing cut-cells
   (11:11:08) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:11:08) Computing gradients
   (11:11:12) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[-0.00093593]]
========================================

At iterate    2    f=  7.74827D-04    |proj g|=  9.35931D-04
----------------------------------------
>>> twist [-0.01381241]
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 3.625629
 Tessellating body 1 with  MaxEdge = 0.018128  Sag = 0.000906  Angle = 10.000000
 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7  -symmY -halfBody > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:11:18) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:12:16) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [1.42534934e-06]  CL 0.00122587
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:12:18) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:13:21) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               38636
              Estimated cutter memory:  0.003864 GB / DV
              Estimated xsensit memory: 0.073408 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (11:13:22) Linearizing cut-cells
   (11:13:24) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:13:24) Computing gradients
   (11:13:28) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[3.98393944e-05]]
========================================

At iterate    3    f=  1.42535D-06    |proj g|=  3.98394D-05
----------------------------------------
>>> twist [-0.08697262]
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 3.625704
 Tessellating body 1 with  MaxEdge = 0.018129  Sag = 0.000906  Angle = 10.000000
 Executing: autoInputs -r 5.123450 -nDiv 5 -maxR 7  -symmY -halfBody > autoInputs.out
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:13:33) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:14:26) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [8.4487288e-07]  CL 0.00093859
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (11:14:28) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (11:15:13) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               37754
              Estimated cutter memory:  0.003775 GB / DV
              Estimated xsensit memory: 0.071733 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (11:15:14) Linearizing cut-cells
   (11:15:16) ... done
   o Number of simultaneous xsensit jobs:  1
   (11:15:16) Computing gradients
   (11:15:20) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[3.04137204e-05]]
========================================

At iterate    4    f=  8.44873D-07    |proj g|=  3.04137D-05

           * * *

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      4      5      4     0     0   3.041D-05   8.449D-07
  F =   8.4487287991999989E-007

CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH             
Optimization Complete
-----------------------------------
Optimized values: [-0.08697262]

real	10m6.806s
user	6m46.713s
sys	0m20.064s
+ status=0
+ set +x

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


=================================================
+ echo 'fun3d_Morph_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
fun3d_Morph_PyTest.py test;
+ python -u fun3d_Morph_PyTest.py -outLevel=0 -noAnalysis
+ 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
AFLR4    : Proximity BG Surface Grid Generation Skipped
AFLR4    : No Modifications Required

Writing TECPLOT file: pyCAPS_AFLR4_AFLR3_Surf_0.dat ....
Finished writing TECPLOT file


Writing TECPLOT file: pyCAPS_AFLR4_AFLR3_Surf_1.dat ....
Finished writing TECPLOT file


Writing TECPLOT file: pyCAPS_AFLR4_AFLR3_Surf_2.dat ....
Finished writing TECPLOT file

Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 3
	Name = Wing1, index = 1
	Name = Wing2, index = 2
	Name = Farfield, index = 3
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 - 7909
Number of surface elements - 15806
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 10.22.23
AFLR4    : Version Date   07/14/22 @ 02:23PM
AFLR4    : Compile OS     Darwin 20.6.0 arm64
AFLR4    : Compile Date   07/19/22 @ 12:00AM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

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

OVERALL  : CPU Time          =     0.217   seconds

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

OVERALL  : CPU Time          =     0.159   seconds
Volume mesh:
	Number of nodes = 81547
	Number of elements = 475822
	Number of triangles = 15806
	Number of quadrilatarals = 0
	Number of tetrahedrals = 460016
	Number of pyramids= 0
	Number of prisms= 0
	Number of hexahedrals= 0

Writing TECPLOT file: pyCAPS_AFLR4_AFLR3_VolMesh.dat ....
Finished writing TECPLOT file

Getting CFD boundary conditions
	Boundary condition name - Farfield
	Boundary condition name - Wing1
	Boundary condition name - Wing2
	Done getting CFD boundary conditions

Getting CFD design variables.......
	Number of design variables - 2
	Design Variable name - Alpha
	Design Variable name - twist
	Done getting CFD design variables
Getting CFD functional.......
	Number of design variables - 2
	Objective name - Cd2
	Objective name - Const
	Done getting CFD functional
Python library was linked, but will not be used!
Creating FUN3D directory tree
DesignVariable = Alpha
DesignVariable = twist
Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1
Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1
Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1
Writing rubber.data 
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat

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.
Reading rubber.data 
Projecting tessellation 1 (of 3) on to new body
Projecting tessellation 2 (of 3) on to new body
Projecting tessellation 3 (of 3) on to new body
Python library was linked, but will not be used!
Creating FUN3D directory tree
DesignVariable = Alpha
DesignVariable = twist
Writing sensitivity file for body 1, File - Rubberize/model.tec.1.sd1
Writing sensitivity file for body 2, File - Rubberize/model.tec.2.sd1
Writing sensitivity file for body 3, File - Rubberize/model.tec.3.sd1
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat
Writing surface file for 1 (of 3) in body 1 File - Flow/fun3dAFLRTest_body1.dat

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.
Reading rubber.data 

real	0m13.740s
user	0m12.603s
sys	0m0.545s
+ status=0
+ set +x

=================================================
CAPS verification (using pyCAPS) case fun3d_Morph_PyTest.py passed (as expected)
=================================================


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

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

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

All tests pass!


=================================================
=================================================
[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] 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 #174' 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 #175'.
[Checks API] No suitable checks publisher found.
Build step 'Console output (build log) parsing' changed build result to FAILURE
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] Skipped based on build state FAILURE
Finished: FAILURE