Console Output

Skipping 489 KB.. Full Log
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (23:41:32) Linearizing cut-cells
   (23:41:32) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:41:32) Computing gradients
   (23:46:32) ... 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
   (23:46:35) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1
   (23:46:47) 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
   (23:46:49) Running aero.csh on 2 core(s) in M0.5901A1.98427B0_DP1
   (23:46:59) 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
   (23:47:00) Linearizing cut-cells
   (23:47:00) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:47:00) Computing gradients
   (23:47:04) ... 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
   (23:47:07) Running aero.csh on 2 core(s) in M0.5901A-0.0109918B0_DP1
   (23:47:18) aero.csh done
 o case M0.5901A-0.0109918B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [6.05653687e-06]  CL 0.00246101
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (23:47:20) Running aero.csh on 2 core(s) in M0.5901A-0.0109918B0_DP1
   (23:47:33) 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
   (23:47:35) Linearizing cut-cells
   (23:47:35) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:47:35) Computing gradients
   (23:47:39) ... done
 o case M0.5901A-0.0109918B0_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
   (23:47:42) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1
   (23:47:53) aero.csh done
 o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [2.59817201e-10]  CL 1.612e-05
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (23:47:55) Running aero.csh on 2 core(s) in M0.5901A-0.0514929B0_DP1
   (23:48:03) 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
   (23:48:03) Linearizing cut-cells
   (23:48:03) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:48:03) Computing gradients
   (23:48:07) ... done
 o case M0.5901A-0.0514929B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[2.03612486e-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
   (23:48:10) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1
   (23:48:19) aero.csh done
 o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [9.26120217e-15]  CL 1e-07
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (23:48:21) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1
   (23:48:27) 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
   (23:48:28) Linearizing cut-cells
   (23:48:28) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:48:28) Computing gradients
   (23:48:32) ... done
 o case M0.5901A-0.0517603B0_DP1, averaging data over 1 cycle(s)
>>> CL2_alpha [[1.21394333e-08]]
========================================

At iterate    4    f=  9.26120D-15    |proj g|=  1.21394D-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   9.261D-15
  F =   9.2612021713000013E-015

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

real	8m36.030s
user	1m39.713s
sys	0m18.768s
+ 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_RegCaps/7.6/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt
cart3d_OpenMDAO_3_twist_PyTest.py test;
+ python -u cart3d_OpenMDAO_3_twist_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt
----------------------------------------
>>> 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
   (23:48:40) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:49:10) 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
   (23:49:14) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:50:08) 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
   (23:50:08) Linearizing cut-cells
   (23:50:10) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:50:10) Computing gradients
   (23:50:14) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[0.00209615]]
========================================
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|=  2.09615D-03
----------------------------------------
>>> twist [3.99790385]
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
   (23:50:19) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:50:49) 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
   (23:50:51) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:51:36) 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
   (23:51:37) Linearizing cut-cells
   (23:51:39) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:51:39) Computing gradients
   (23:51:43) ... 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 [-1.83549219]
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 3.627738
 Tessellating body 1 with  MaxEdge = 0.018139  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
   (23:51:47) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:52:16) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.00079649]  CL -0.0282221
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (23:52:19) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:53:10) aero.csh done
              Max memory allowed:       32 GB
              Flow hexes:               37721
              Estimated cutter memory:  0.003772 GB / DV
              Estimated xsensit memory: 0.071670 GB / DV
              Available threads:        2
              # DVs:                    1
   o Number of simultaneous cutter jobs:   1
   (23:53:10) Linearizing cut-cells
   (23:53:12) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:53:13) Computing gradients
   (23:53:17) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[-0.00094963]]
========================================

At iterate    2    f=  7.96486D-04    |proj g|=  9.49629D-04
----------------------------------------
>>> twist [-0.01627377]
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 3.625631
 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
   (23:53:20) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:54:03) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [1.46434194e-06]  CL 0.00122346
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (23:54:06) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:55:03) 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
   (23:55:04) Linearizing cut-cells
   (23:55:06) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:55:06) Computing gradients
   (23:55:10) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[4.03779583e-05]]
========================================

At iterate    3    f=  1.46434D-06    |proj g|=  4.03780D-05
----------------------------------------
>>> twist [-0.09047153]
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 3.625707
 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
   (23:55:13) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:56:01) aero.csh done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [7.13753222e-07]  CL 0.00085977
----------------------------------------
========================================
 o Evaluating Cart3D functionals and/or gradients
   ATTENTION: using static geometry ../inputs/Components.i.tri
   (23:56:05) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
   (23:57:08) 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
   (23:57:09) Linearizing cut-cells
   (23:57:11) ... done
   o Number of simultaneous xsensit jobs:  1
   (23:57:11) Computing gradients
   (23:57:15) ... done
 o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[2.79530608e-05]]
========================================

At iterate    4    f=  7.13753D-07    |proj g|=  2.79531D-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   2.795D-05   7.138D-07
  F =   7.1375322237999993E-007

CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH             
Optimization Complete
-----------------------------------
Optimized values: [-0.09047153]

real	8m43.641s
user	9m58.418s
sys	0m36.148s
+ status=0
+ set +x

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


=================================================
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt
+ echo 'fun3d_Morph_PyTest.py test;'
fun3d_Morph_PyTest.py test;
+ python -u fun3d_Morph_PyTest.py -outLevel=0 -noAnalysis
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/ESP/DARWIN64/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 19.6.0 x86_64
AFLR2    : Compile Date   07/02/22 @ 03:34PM
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 19.6.0 x86_64
AFLR4    : Compile Date   07/18/22 @ 06:42PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.22
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

OVERALL  : CPU Time          =     0.166   seconds

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.22
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

OVERALL  : CPU Time          =     0.171   seconds
Volume mesh:
	Number of nodes = 84310
	Number of elements = 492190
	Number of triangles = 15806
	Number of quadrilatarals = 0
	Number of tetrahedrals = 476384
	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	0m17.788s
user	0m15.042s
sys	0m1.579s
+ 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!


=================================================
=================================================
++ cd /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest
++ ./execute_PyTestRegression.sh CFD

=================================================
Legacy Using python : /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/ESP/venv/bin/python
=================================================

Running.... CFD PyTests

=================================================
+ rm -rf su2_and_AFLR2_NodeDist_PyTest
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
+ echo 'su2_and_AFLR2_NodeDist_PyTest.py test;'
su2_and_AFLR2_NodeDist_PyTest.py test;
+ python -u su2_and_AFLR2_NodeDist_PyTest.py -verbosity=0 -workDir=runDirectory
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5

Getting mesh sizing parameters
	Mesh sizing name - 2DSlice
	Mesh sizing name - Airfoil
	Mesh sizing name - InFlow
	Mesh sizing name - OutFlow
	Mesh sizing name - TunnelWall
	Done getting mesh sizing parameters
Getting 2D mesh for body 1 (of 1)
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.3
AFLR2    : Version Date   06/09/22 @ 05:16PM
AFLR2    : Compile OS     Darwin 19.6.0 x86_64
AFLR2    : Compile Date   07/02/22 @ 03:34PM
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          =     0.015   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_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/pyCAPS/su2_and_AFLR2_NodeDist_PyTest/Scratch/runDirectory_SU2AFLR2NodeDistAnalysisTest1_aflr2AIM/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          =     0.002   seconds
Number of nodes = 3715
Number of elements = 7430
Number of tris = 7206
Number of quad = 0

Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Airfoil
	Boundary condition name - InFlow
	Boundary condition name - OutFlow
	Boundary condition name - TunnelWall
	Warning: No boundary condition specified for capsGroup 2DSlice!
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "


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: ../runDirectory_SU2AFLR2NodeDistAnalysisTest1_aflr2AIM/aflr2.su2

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

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

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

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_pyCAPS_SU2_aflr2.dat.
Surface file name: surface_flow_pyCAPS_SU2_aflr2.
Volume file name: flow_pyCAPS_SU2_aflr2.
Restart file name: restart_flow_pyCAPS_SU2_aflr2.dat.

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

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

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

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

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Two dimensional problem.
3715 grid points.
7206 volume elements.
4 surface markers.
98 boundary elements in index 0 (Marker = BC_2).
24 boundary elements in index 1 (Marker = BC_3).
24 boundary elements in index 2 (Marker = BC_4).
78 boundary elements in index 3 (Marker = BC_5).
7206 triangles.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 7206 TRIANGLE volume elements.
There has been a re-orientation of 224 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 999.917.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 177.06. Mean K: 1.97231. Standard deviation K: 13.0434.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        63.4343|             90|
|     CV Face Area Aspect Ratio|              1|        5.23543|
|           CV Sub-Volume Ratio|              1|        3.11804|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      3715|    1/1.00|        10|
|         1|      1048|    1/3.54|   7.96696|
|         2|       299|    1/3.51|    6.3832|
+-------------------------------------------+
Finding max control volume width.
Wetted area = 2.06136 m.
Area projection in the x-plane = 0.178383 m, y-plane = 0.994925 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.138389 m.
Min. coordinate in the x-direction = -0.000250564 m, y-direction = -0.0151999 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_5 is NOT a single straight.
Boundary marker BC_2 is NOT a single straight.
Computing wall distances.

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

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        216054|             1|   m^2/s^2|        216054|
|            Velocity-X|       136.119|             1|       m/s|       136.119|
|            Velocity-Y|             0|             1|       m/s|             0|
|    Velocity Magnitude|       136.119|             1|       m/s|       136.119|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|           0.4|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

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

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

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

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  5.9516e-02|   -0.385358|    2.453598|    1.625650|    5.369499|    0.360385|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  6.3542e-02|   -0.521485|    2.079409|    1.371893|    4.965390|    1.182869|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  6.2367e-02|   -0.795894|    1.733901|    1.139977|    4.664635|    3.893200|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  6.3484e-02|   -0.885699|    1.481333|    1.013744|    4.332779|   14.565586|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  6.3596e-02|   -0.993750|    1.340252|    0.917512|    4.182929|  110.244281|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  6.4209e-02|   -1.110400|    1.172200|    0.857005|    3.936065| -495.810537|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  6.3947e-02|   -1.185766|    1.111335|    0.833878|    3.815560|  126.878572|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  6.3972e-02|   -1.253010|    1.087205|    0.820497|    3.761994|   40.129581|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  6.3927e-02|   -1.297506|    1.067371|    0.803439|    3.702559|   25.133515|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  6.3934e-02|   -1.307387|    1.040694|    0.767965|    3.668429|   21.072302|

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

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

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

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

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

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat).
+-----------------------------------------------------------------------+

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------

Total Force - Pressure + Viscous
Cl =  0.650422 Cd =  0.030866
Cmz =  0.373254
Cx =  0.030866 Cy =  0.650422
Pressure Contribution
Cl_p =  0.650422 Cd_p =  0.030866
Cmz_p =  0.373254
Cx_p =  0.030866 Cy_p =  0.650422
Viscous Contribution
Cl_v =  0.0 Cd_v =  0.0
Cmz_v =  0.0
Cx_v =  0.0 Cy_v =  0.0
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.capsIntent' is deprecated. Please use 'None'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	0m2.928s
user	0m1.716s
sys	0m0.812s
+ status=0
+ set +x

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


=================================================
+ rm -rf su2_and_AFLR2_PyTest
+ echo 'su2_and_AFLR2_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
su2_and_AFLR2_PyTest.py test;
+ python -u su2_and_AFLR2_PyTest.py -verbosity=0 -workDir=runDirectory
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
Saving geometry
Directory does not currently exist while creating a filename - it will be made automatically
Mapping capsMesh attributes ................
	Number of unique capsMesh attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 5
	Name = 2DSlice, index = 1
	Name = TunnelWall, index = 2
	Name = OutFlow, index = 3
	Name = InFlow, index = 4
	Name = Airfoil, index = 5

Getting mesh sizing parameters
	Mesh sizing name - 2DSlice
	Mesh sizing name - Airfoil
	Mesh sizing name - InFlow
	Mesh sizing name - OutFlow
	Mesh sizing name - TunnelWall
	Done getting mesh sizing parameters
Getting 2D mesh for body 1 (of 1)
 
AFLR2    : ---------------------------------------
AFLR2    : AFLR2 LIBRARY
AFLR2    : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2    : TRIA/QUAD GRID GENERATOR
AFLR2    : Version Number 9.14.3
AFLR2    : Version Date   06/09/22 @ 05:16PM
AFLR2    : Compile OS     Darwin 19.6.0 x86_64
AFLR2    : Compile Date   07/02/22 @ 03:34PM
AFLR2    : Copyright 1994-2021, D.L. Marcum
AFLR2    : ---------------------------------------
 
AFLR2 IC : INPUT DATA CHECK
 
AFLR2 IC : Nodes, Faces      =       545         0
 
AFLR2    : CPU Time          =     0.001   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          =     0.004   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          =     0.073   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          =     0.030   seconds
 
AFLR2    : DONE
Number of nodes = 11153
Number of elements = 11932
Number of tris = 1013
Number of quad = 10374

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


Writing SU2 file ....
Finished writing SU2 file

Getting CFD boundary conditions
	Boundary condition name - Airfoil
	Boundary condition name - InFlow
	Boundary condition name - OutFlow
	Boundary condition name - TunnelWall
	Warning: No boundary condition specified for capsGroup 2DSlice!
	Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "


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: ../runDirectory_SU2AFLR2ArbShapeAnalysisTest1_aflr2AIM/aflr2.su2

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

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

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

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                  TECPLOT|       250|
|          SURFACE_TECPLOT|       250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_pyCAPS_su2_aflr2.dat.
Surface file name: surface_flow_pyCAPS_su2_aflr2.
Volume file name: flow_pyCAPS_su2_aflr2.
Restart file name: restart_flow_pyCAPS_su2_aflr2.dat.

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

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

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

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

------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Two dimensional problem.
11153 grid points.
11387 volume elements.
4 surface markers.
98 boundary elements in index 0 (Marker = BC_2).
24 boundary elements in index 1 (Marker = BC_3).
24 boundary elements in index 2 (Marker = BC_4).
399 boundary elements in index 3 (Marker = BC_5).
1013 triangles.
10374 quadrilaterals.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 1013 TRIANGLE volume elements.
There has been a re-orientation of 10374 QUADRILATERAL volume elements.
There has been a re-orientation of 545 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 999.877.
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: 2.15881. Standard deviation K: 17.7215.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        49.1197|             90|
|     CV Face Area Aspect Ratio|        1.00061|         32.974|
|           CV Sub-Volume Ratio|        1.00002|        6.32859|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     11153|    1/1.00|        10|
|         1|      2707|    1/4.12|   7.38992|
|         2|       555|    1/4.88|   5.01918|
+-------------------------------------------+
Finding max control volume width.
Wetted area = 2.06265 m.
Area projection in the x-plane = 0.211192 m, y-plane = 0.997011 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.102037 m.
Min. coordinate in the x-direction = 0.000323229 m, y-direction = -0.108492 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_5 is NOT a single straight.
Boundary marker BC_2 is NOT a single straight.
Computing wall distances.

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

-- Models:
+------------------------------------------------------------------------------+
|          Viscosity Model|        Conductivity Model|              Fluid Model|
+------------------------------------------------------------------------------+
|                        -|                         -|             STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|          Gas Constant|       287.058|             1|  N.m/kg.K|       287.058|
|      Spec. Heat Ratio|             -|             -|         -|           1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
|                  Name|    Dim. value|    Ref. value|      Unit|Non-dim. value|
+------------------------------------------------------------------------------+
|       Static Pressure|        101325|             1|        Pa|        101325|
|               Density|       1.22498|             1|    kg/m^3|       1.22498|
|           Temperature|        288.15|             1|         K|        288.15|
|          Total Energy|        216054|             1|   m^2/s^2|        216054|
|            Velocity-X|       136.119|             1|       m/s|       136.119|
|            Velocity-Y|             0|             1|       m/s|             0|
|    Velocity Magnitude|       136.119|             1|       m/s|       136.119|
+------------------------------------------------------------------------------+
|           Mach Number|             -|             -|         -|           0.4|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.

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

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

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

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

Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
|   Time_Iter|  Outer_Iter|  Inner_Iter|    Cur_Time|   Time_Step|   Time(sec)|    rms[Rho]|   rms[RhoU]|   rms[RhoV]|   rms[RhoE]|        CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
|           0|           0|           0|  0.0000e+00|  0.0000e+00|  1.6303e-01|    0.070615|    2.738611|    1.108464|    5.599347|    0.058184|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  1.5117e-01|   -0.454267|    2.190680|    1.555679|    5.064740|    0.060630|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  1.4619e-01|   -0.565341|    2.070468|    1.485403|    4.949698|    0.060586|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  1.4435e-01|   -0.726390|    1.920921|    1.383781|    4.787685|    0.072845|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.4470e-01|   -0.883308|    1.823260|    1.266042|    4.630445|    0.126180|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  1.4329e-01|   -1.042499|    1.755083|    1.151079|    4.468758|    0.301945|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  1.4273e-01|   -1.231529|    1.700482|    1.105648|    4.268760|    0.849538|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  1.4288e-01|   -1.327203|    1.639352|    1.129519|    4.117576|    2.769795|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  1.4268e-01|   -1.267223|    1.565550|    1.141885|    4.144438|   46.482609|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  1.4292e-01|   -1.220125|    1.493905|    1.121919|    4.191590|   -5.798185|

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

Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.22013|         < -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 994 more values.0: Error finishing Tecplot file output.

Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat).
+-----------------------------------------------------------------------+

------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------

------------------------- Exit Success (SU2_CFD) ------------------------

Total Force - Pressure + Viscous
Cl =  0.083415 Cd =  -0.014386
Cmz =  0.080305
Cx =  -0.014386 Cy =  0.083415
Pressure Contribution
Cl_p =  0.083415 Cd_p =  -0.014386
Cmz_p =  0.080305
Cx_p =  -0.014386 Cy_p =  0.083415
Viscous Contribution
Cl_v =  0.0 Cd_v =  0.0
Cmz_v =  0.0
Cx_v =  0.0 Cy_v =  0.0
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.setGeometryVal' is deprecated. Please use 'Problem.geometry.despmtr["varname"].value'!
WARNING: 'capsGeometry.saveGeometry' is deprecated. Please use 'Problem.geometry.save'!
WARNING: 'capsProblem.capsIntent' is deprecated. Please use 'None'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	0m4.173s
user	0m3.131s
sys	0m0.983s
+ status=0
+ set +x

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


=================================================
+ rm -rf su2_and_AFLR4_AFLR3_PyTest
+ echo 'su2_and_AFLR4_AFLR3_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
su2_and_AFLR4_AFLR3_PyTest.py test;
+ python -u su2_and_AFLR4_AFLR3_PyTest.py -verbosity=0 -workDir=runDirectory
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/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: 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

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 - 7902
Number of surface elements - 15792
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 19.6.0 x86_64
AFLR2    : Compile Date   07/02/22 @ 03:34PM
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 19.6.0 x86_64
AFLR4    : Compile Date   07/18/22 @ 06:42PM
AFLR4    : Copyright 1994-2021, D.L. Marcum
AFLR4    : ---------------------------------------

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.22
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

OVERALL  : CPU Time          =     0.289   seconds

EGADS    : ---------------------------------------
EGADS    : Engineering Geometry Aircraft Design System
EGADS    : Version 1.22
EGADS    : OpenCASCADE Version 7.6.0
EGADS    : ---------------------------------------

OVERALL  : CPU Time          =     0.147   seconds
Volume mesh:
	Number of nodes = 80698
	Number of elements = 470728
	Number of triangles = 15792
	Number of quadrilatarals = 0
	Number of tetrahedrals = 454936
	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 - 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: ../runDirectory_SU2andAFRLMeshTest2_aflr3AIM/aflr3_0.su2

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

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

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

-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency: 
+------------------------------------+
|                     File| Frequency|
+------------------------------------+
|                  RESTART|       250|
|              SURFACE_CSV|       250|
|                 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_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.
80698 grid points.
454936 volume elements.
3 surface markers.
9970 boundary elements in index 0 (Marker = BC_1).
5418 boundary elements in index 1 (Marker = BC_2).
404 boundary elements in index 2 (Marker = BC_3).
454936 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: 50.9908. Standard deviation K: 240.169.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        49.1111|        87.0038|
|     CV Face Area Aspect Ratio|        1.04666|        79.6918|
|           CV Sub-Volume Ratio|        1.03853|        1194.21|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     80698|    1/1.00|        10|
|         1|     13179|    1/6.12|   8.19907|
|         2|      2014|    1/6.54|   6.57529|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.90569 m.
Wetted area = 119.559 m^2.
Area projection in the x-plane = 11.2439 m^2, y-plane = 5.04481 m^2, z-plane = 56.2538 m^2.
Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.583234 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|  3.9430e+00|   -0.387339|    1.985892|    1.668046|    5.103557|    1.907215|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  4.0586e+00|   -0.204522|    2.256668|    1.918937|    5.301456|    2.555220|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  4.0198e+00|   -0.110763|    2.401310|    2.230676|    5.393701|    4.014858|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  3.9114e+00|   -0.137728|    2.438789|    2.409691|    5.349883|    6.109362|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  3.8235e+00|   -0.176731|    2.434444|    2.486209|    5.289401|    8.063870|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|     -0.176731|         < -14|          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 =  0.871808 Cd =  0.108113
Cmx =  0.000794 Cmy =  -0.248897 Cmz =  -0.000136
Cx =  0.092881 Cy =  -0.000126 Cz =  0.873562
Pressure Contribution
Cl_p =  0.871808 Cd_p =  0.108113
Cmx_p =  0.000794 Cmy_p =  -0.248897 Cmz_p =  -0.000136
Cx_p =  0.092881 Cy_p =  -0.000126 Cz_p =  0.873562
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
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.setGeometryVal' is deprecated. Please use 'Problem.geometry.despmtr["varname"].value'!
WARNING: 'capsGeometry.buildGeometry' is deprecated. Please use 'Problem.geometry.build'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	0m55.298s
user	0m46.735s
sys	0m2.953s
+ status=0
+ set +x

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


=================================================
+ rm -rf su2_and_Delaundo_PyTest
+ echo 'su2_and_Delaundo_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
su2_and_Delaundo_PyTest.py test;
+ python -u su2_and_Delaundo_PyTest.py -verbosity=0 -workDir=runDirectory
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/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


Running Delaundo......
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: ../runDirectory_SU2DelaundoAnalysisTest1_delaundoAIM/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_pyCAPS_SU2_Delaundo.dat.
Surface file name: surface_flow_pyCAPS_SU2_Delaundo.
Volume file name: flow_pyCAPS_SU2_Delaundo.
Restart file name: restart_flow_pyCAPS_SU2_Delaundo.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.
6320 grid points.
12346 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).
12346 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: 10.8142. 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|        89.3051|
|     CV Face Area Aspect Ratio|         1.0235|        15.7138|
|           CV Sub-Volume Ratio|              1|        7.93643|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      6320|    1/1.00|        10|
|         1|      1790|    1/3.53|   7.98287|
|         2|       504|    1/3.55|   6.35388|
+-------------------------------------------+
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 = -0.00104578 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|  1.3178e-01|   -1.163171|    1.073770|    1.341444|    4.312165|    0.062120|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  1.5110e-01|   -1.561828|    0.808636|    0.967487|    3.922716|    0.139775|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  1.4739e-01|   -1.601698|    0.943793|    1.009036|    3.876382|    0.373708|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  1.4376e-01|   -1.659374|    1.008221|    1.015635|    3.799753|    0.952935|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  1.4201e-01|   -1.663585|    1.011627|    0.956487|    3.788246|    2.344781|
|           0|           0|           5|  0.0000e+00|  0.0000e+00|  1.3902e-01|   -1.633451|    0.991734|    0.872954|    3.829708|    6.259549|
|           0|           0|           6|  0.0000e+00|  0.0000e+00|  1.3762e-01|   -1.626398|    0.990123|    0.847075|    3.843511|   26.349556|
|           0|           0|           7|  0.0000e+00|  0.0000e+00|  1.3496e-01|   -1.643439|    1.009125|    0.895796|    3.825758|  -56.104876|
|           0|           0|           8|  0.0000e+00|  0.0000e+00|  1.3143e-01|   -1.659565|    1.020774|    0.939260|    3.804303|  -24.431167|
|           0|           0|           9|  0.0000e+00|  0.0000e+00|  1.2870e-01|   -1.676757|    1.012633|    0.938320|    3.783310|  -21.456835|

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

Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|      -1.67676|         < -14|          No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
|        File Writing Summary       |              Filename             |
+-----------------------------------------------------------------------+
|SU2 binary restart                 |restart_flow_pyCAPS_SU2_Delaundo.dat|

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Delaundo.dat).
|CSV file                           |surface_flow_pyCAPS_SU2_Delaundo.csv|

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Delaundo.dat).
|Tecplot binary                     |flow_pyCAPS_SU2_Delaundo.szplt     |

Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Delaundo.dat).
|Tecplot binary surface             |surface_flow_pyCAPS_SU2_Delaundo.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_pyCAPS_SU2_Delaundo.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 =  0.805231 Cd =  -0.037528
Cmz =  0.414714
Cx =  -0.037528 Cy =  0.805231
Pressure Contribution
Cl_p =  0.805231 Cd_p =  -0.037528
Cmz_p =  0.414714
Cx_p =  -0.037528 Cy_p =  0.805231
Viscous Contribution
Cl_v =  0.0 Cd_v =  0.0
Cmz_v =  0.0
Cx_v =  0.0 Cy_v =  0.0
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	0m3.970s
user	0m2.575s
sys	0m0.942s
+ status=0
+ set +x

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


=================================================
+ rm -rf su2_and_Tetgen_PyTest
+ echo 'su2_and_Tetgen_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
su2_and_Tetgen_PyTest.py test;
+ python -u su2_and_Tetgen_PyTest.py -verbosity=0 -workDir=runDirectory
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/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    = 267
Number of elements = 530
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 530
Number of quadrilateral elements = 0
----------------------------
Total number of nodes    = 3139
Total number of elements = 6266

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 - 3139, elements - 6266
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds:  0.047359
Creating surface mesh ...
Surface mesh seconds:  0.013568
Recovering boundaries...
Boundary recovery seconds:  0.143637
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds:  0.014539
Suppressing Steiner points ...
Steiner suppression seconds:  2.7e-05
Recovering Delaunayness...
Delaunay recovery seconds:  0.016468
Refining mesh...
  4189 insertions, added 2138 points, 127097 tetrahedra in queue.
  1394 insertions, added 409 points, 130640 tetrahedra in queue.
  1859 insertions, added 449 points, 127916 tetrahedra in queue.
  2478 insertions, added 473 points, 111923 tetrahedra in queue.
  3303 insertions, added 484 points, 65315 tetrahedra in queue.
  4403 insertions, added 433 points, 571 tetrahedra in queue.
Refinement seconds:  1.57502
Smoothing vertices...
Mesh smoothing seconds:  0.898363
Improving mesh...
Mesh improvement seconds:  0.021868
Jettisoning redundant points.

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

Output seconds:  0.005076
Total running seconds:  2.7366

Statistics:

  Input points: 3139
  Input facets: 6266
  Input segments: 9399
  Input holes: 2
  Input regions: 0

  Mesh points: 8039
  Mesh tetrahedra: 39668
  Mesh faces: 82470
  Mesh faces on exterior boundary: 6268
  Mesh faces on input facets: 6268
  Mesh edges on input segments: 9400
  Steiner points on input segments:  1
  Steiner points inside domain: 4899

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: ../runDirectory_SU2TetgenAnalysisTest2_tetgenAIM/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.
8039 grid points.
39668 volume elements.
3 surface markers.
4468 boundary elements in index 0 (Marker = BC_1).
1270 boundary elements in index 1 (Marker = BC_2).
530 boundary elements in index 2 (Marker = BC_3).
39668 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: 2.08934e+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: 30.561. Standard deviation K: 37.5336.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        1.83144|        84.8022|
|     CV Face Area Aspect Ratio|        1.55015|        7101.39|
|           CV Sub-Volume Ratio|        1.05639|         198266|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|      8039|    1/1.00|        10|
|         1|      1338|    1/6.01|   8.25105|
|         2|       214|    1/6.25|    6.7182|
+-------------------------------------------+
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|  3.6523e-01|    0.619384|    3.051344|    2.094590|    6.110279|    1.812161|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  3.4410e-01|    0.785542|    3.264371|    2.974872|    6.285549|    2.181906|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  3.3468e-01|    0.724139|    3.334285|    3.249736|    6.229534|    3.226648|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  3.3078e-01|    0.621976|    3.305627|    3.334988|    6.113861|    4.648342|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  3.2876e-01|    0.625390|    3.207240|    3.303991|    6.098630|    5.785533|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       0.62539|         < -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 =  0.759441 Cd =  0.131266
Cmx =  0.001646 Cmy =  -0.215157 Cmz =  0.000487
Cx =  0.117991 Cy =  0.00137 Cz =  0.761616
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.setGeometryVal' is deprecated. Please use 'Problem.geometry.despmtr["varname"].value'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsAnalysis.aimName' is deprecated. Please use 'name'!
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsAnalysis.getAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	2m30.169s
user	2m11.861s
sys	0m3.373s
+ status=0
+ set +x

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


=================================================
+ rm -rf su2_X43a_PyTest
+ echo 'su2_X43a_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
su2_X43a_PyTest.py test;
+ python -u su2_X43a_PyTest.py -verbosity=0 -workDir=runDirectory
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/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    = 3808
Number of elements = 7616
Number of node elements          = 0
Number of line elements          = 0
Number of triangle elements      = 7616
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    = 9462
Total number of elements = 18920

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


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

No analysis directory provided - defaulting to altName
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 2
	Name = x43A, index = 1
	Name = Farfield, index = 2
Number of surface: nodes - 9462, elements - 18920
Getting volume mesh

Generating volume mesh using TetGen.....

Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds:  0.138353
Creating surface mesh ...
Surface mesh seconds:  0.040682
Recovering boundaries...
Warning:  6 segments are not recovered.
Boundary recovery seconds:  0.333195
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds:  0.031085
Suppressing Steiner points ...
Steiner suppression seconds:  3.1e-05
Recovering Delaunayness...
Delaunay recovery seconds:  0.036701
Refining mesh...
  12618 insertions, added 5266 points, 45 tetrahedra in queue.
Refinement seconds:  1.02605
Smoothing vertices...
Mesh smoothing seconds:  1.05604
Improving mesh...
Mesh improvement seconds:  0.034311
Jettisoning redundant points.

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

Output seconds:  0.014747
Total running seconds:  2.71898

Statistics:

  Input points: 9462
  Input facets: 18920
  Input segments: 28380
  Input holes: 1
  Input regions: 0

  Mesh points: 14871
  Mesh tetrahedra: 61451
  Mesh faces: 132365
  Mesh faces on exterior boundary: 18926
  Mesh faces on input facets: 18926
  Mesh edges on input segments: 28383
  Steiner points on input segments:  3
  Steiner points inside domain: 5406

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: ../tetgenAIM_tetgenAIM/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.
14871 grid points.
61451 volume elements.
2 surface markers.
7622 boundary elements in index 0 (Marker = BC_1).
11304 boundary elements in index 1 (Marker = BC_2).
61451 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: 0.525068. Standard deviation K: 2.57981.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
|           Mesh Quality Metric|        Minimum|        Maximum|
+--------------------------------------------------------------+
|    Orthogonality Angle (deg.)|        2.06744|        83.7887|
|     CV Face Area Aspect Ratio|        1.43723|        2173.76|
|           CV Sub-Volume Ratio|              1|         173135|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
|  MG Level|       CVs|Aggl. Rate|       CFL|
+-------------------------------------------+
|         0|     14871|    1/1.00|        10|
|         1|      2668|    1/5.57|   8.46005|
|         2|       485|     1/5.5|   7.18869|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 30 m.
Wetted area = 13597.1 m^2.
Area projection in the x-plane = 761.677 m^2, y-plane = 2062.72 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|  5.7974e-01|    2.731069|    5.665107|    4.728786|    8.730545|   -0.436683|
|           0|           0|           1|  0.0000e+00|  0.0000e+00|  5.7768e-01|    3.111430|    6.144622|    5.696750|    9.111258|   -0.141963|
|           0|           0|           2|  0.0000e+00|  0.0000e+00|  5.7238e-01|    3.211662|    6.272652|    5.788428|    9.178461|   -0.024009|
|           0|           0|           3|  0.0000e+00|  0.0000e+00|  5.6218e-01|    3.212184|    6.263165|    5.685299|    9.173101|   -0.000960|
|           0|           0|           4|  0.0000e+00|  0.0000e+00|  5.4371e-01|    3.198243|    6.249209|    5.549303|    9.170283|   -0.026819|

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

Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
|      Convergence Field     |     Value    |   Criterion  |  Converged |
+-----------------------------------------------------------------------+
|                    rms[Rho]|       3.19824|         < -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 138 non-physical points in the solution.
Warning: 52 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 =  -3.146787 Cd =  117.33593
Cmx =  -34.741605 Cmy =  9278.394828 Cmz =  115.177861
Cx =  117.339815 Cy =  1.882467 Cz =  2.998413
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.capsIntent' is deprecated. Please use 'None'!
WARNING: 'capsGeometry.setGeometryVal' is deprecated. Please use 'Problem.geometry.despmtr["varname"].value'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsAnalysis.aimName' is deprecated. Please use 'name'!
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	0m17.081s
user	0m16.837s
sys	0m1.830s
+ status=0
+ set +x

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

./execute_PyTestRegression.sh: line 304: ulimit: stack size: cannot modify limit: Operation not permitted

=================================================
+ rm -rf cart_PyTest
+ echo 'cart_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
cart_PyTest.py test;
+ python -u cart_PyTest.py -verbosity=0 -workDir=runDirectory
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
Loading AIM
Mapping capsGroup attributes ................
	Number of unique capsGroup attributes = 1
	Name = Wing, index = 1
 Body size = 7.674092
 Tessellating body 1 with  MaxEdge = 0.191852  Sag = 0.007674  Angle = 15.000000
 Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 12  > autoInputs.out
Running CART3D
C_A  0.11228753
C_Y  0.0048772887
C_N  -0.00061949123
C_D  0.11219751
C_S  0.0048772887
C_L  -0.0045378921
C_l  0.000770684
C_m  0.00023963
C_n  0.24454
C_M_x  0.00930454
C_M_y  0.00023963
C_M_z  0.244364
WARNING: 'capsProblem.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.loadCAPS' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsGeometry.__init__' is deprecated. Please use 'Problem.__init__'!
WARNING: 'capsProblem.loadAIM' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.__init__' is deprecated. Please use 'Problem.analysis.create'!
WARNING: 'capsAnalysis.setAnalysisVal' is deprecated. Please use 'Analysis.input["varname"].value'!
WARNING: 'capsAnalysis.getAnalysisOutVal' is deprecated. Please use 'Analysis.output["varname"].value'!
WARNING: 'capsProblem.closeCAPS' is deprecated. Please use 'close'!

real	3m24.336s
user	5m6.942s
sys	0m10.688s
+ status=0
+ set +x

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


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

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

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

All tests pass!


=================================================
=================================================
[Execution node] check if [macys_VM] is in [[windows10x64]]
Run condition [Execution node ] preventing perform for step [Execute Windows batch command]
[GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64')
[Clang] Skipping post processing
[Clang] No filter has been set, publishing all 0 issues
[Clang] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.6,CAPS/CFD,DARWIN64,macys_VM)
[Static Analysis] Using reference build 'ESP_RegCaps/CASREV=7.6,ESPTEST=CAPS/CFD,ESP_ARCH=DARWIN64,buildnode=macys_VM #468' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1
[Static Analysis] -> All quality gates have been passed
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_RegCaps/CASREV=7.6,ESPTEST=CAPS/CFD,ESP_ARCH=DARWIN64,buildnode=macys_VM #469'.
[Checks API] No suitable checks publisher found.
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] done
Finished: SUCCESS