(00:58:55) 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
(00:58:56) Linearizing cut-cells
(00:58:56) ... done
o Number of simultaneous xsensit jobs: 1
(00:58:56) Computing gradients
(00:59:00) ... 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
(00:59:02) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1
(00:59:08) 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
(00:59:10) Running aero.csh on 2 core(s) in M0.5901A-0.0517603B0_DP1
(00:59:17) 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
(00:59:17) Linearizing cut-cells
(00:59:17) ... done
o Number of simultaneous xsensit jobs: 1
(00:59:17) Computing gradients
(00:59:21) ... 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 2m36.207s
user 1m6.348s
sys 0m13.693s
+ 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
(00:59:28) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(00:59:58) 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
(01:00:01) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(01:00:58) 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
(01:00:59) Linearizing cut-cells
(01:01:01) ... done
o Number of simultaneous xsensit jobs: 1
(01:01:01) Computing gradients
(01:01:05) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[0.00210056]]
========================================
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|= 2.10056D-03
----------------------------------------
>>> twist [3.99789944]
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
(01:01:09) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(01:02:00) aero.csh done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.0041123] CL 0.0641197
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(01:02:02) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(01:03:00) 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
(01:03:01) Linearizing cut-cells
(01:03:03) ... done
o Number of simultaneous xsensit jobs: 1
(01:03:03) Computing gradients
(01:03:07) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[0.00210014]]
========================================
At iterate 1 f= 4.11230D-03 |proj g|= 2.10014D-03
----------------------------------------
>>> twist [-6.47168783]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Body size = 3.635635
Tessellating body 1 with MaxEdge = 0.018178 Sag = 0.000909 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
(01:03:11) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(01:03:42) aero.csh done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [0.00980717] CL -0.0990184
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(01:03:44) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(01:04:43) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 37091
Estimated cutter memory: 0.003709 GB / DV
Estimated xsensit memory: 0.070473 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(01:04:44) Linearizing cut-cells
(01:04:46) ... done
o Number of simultaneous xsensit jobs: 1
(01:04:46) Computing gradients
(01:04:50) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[-0.00318445]]
========================================
----------------------------------------
>>> twist [-0.15771385]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Body size = 3.625776
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
(01:04:55) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(01:05:41) aero.csh done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [2.91211965e-07] CL -0.00052368
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(01:05:44) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(01:06:42) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 37755
Estimated cutter memory: 0.003776 GB / DV
Estimated xsensit memory: 0.071735 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(01:06:43) Linearizing cut-cells
(01:06:45) ... done
o Number of simultaneous xsensit jobs: 1
(01:06:45) Computing gradients
(01:06:49) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[-1.78565958e-05]]
========================================
At iterate 2 f= 2.91212D-07 |proj g|= 1.78566D-05
----------------------------------------
>>> twist [-0.12267834]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Body size = 3.625740
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
(01:06:53) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(01:07:30) aero.csh done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2 [5.59536684e-08] CL 0.00019981
----------------------------------------
========================================
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(01:07:32) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
(01:08:15) aero.csh done
Max memory allowed: 32 GB
Flow hexes: 37755
Estimated cutter memory: 0.003776 GB / DV
Estimated xsensit memory: 0.071735 GB / DV
Available threads: 2
# DVs: 1
o Number of simultaneous cutter jobs: 1
(01:08:15) Linearizing cut-cells
(01:08:17) ... done
o Number of simultaneous xsensit jobs: 1
(01:08:17) Computing gradients
(01:08:21) ... done
o case M0.5901A0B0_DP1, averaging data over 1 cycle(s)
>>> CL2_twist [[7.83490338e-06]]
========================================
At iterate 3 f= 5.59537D-08 |proj g|= 7.83490D-06
* * *
Tit = total number of iterations
Tnf = total number of function evaluations
Tnint = total number of segments explored during Cauchy searches
Skip = number of BFGS updates skipped
Nact = number of active bounds at final generalized Cauchy point
Projg = norm of the final projected gradient
F = final function value
* * *
N Tit Tnf Tnint Skip Nact Projg F
1 3 5 3 0 0 7.835D-06 5.595D-08
F = 5.5953668443999999E-008
CONVERGENCE: REL_REDUCTION_OF_F_<=_FACTR*EPSMCH
Optimization Complete
-----------------------------------
Optimized values: [-0.12267834]
real 8m59.452s
user 7m21.034s
sys 0m16.907s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case cart3d_OpenMDAO_3_twist_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'fun3d_Morph_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/ESP/DARWIN64/examples/regressionTest/pyCAPSlog.txt
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.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
Getting volume mesh
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.7
AFLR2 : Version Date 07/16/23 @ 01:42PM
AFLR2 : Compile OS Darwin 22.5.0 x86_64
AFLR2 : Compile Date 07/25/23 @ 11:59AM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR4 : ---------------------------------------
AFLR4 : AFLR4 LIBRARY
AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4 : Version Number 11.5.9
AFLR4 : Version Date 08/14/23 @ 12:27AM
AFLR4 : Compile OS Darwin 22.5.0 x86_64
AFLR4 : Compile Date 08/14/23 @ 01:13PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.25
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.25
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
Volume mesh:
Number of nodes = 79623
Number of elements = 464233
Number of triangles = 15680
Number of quadrilatarals = 0
Number of tetrahedrals = 448553
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 0m16.937s
user 0m14.259s
sys 0m1.169s
+ 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
+ echo 'su2_and_AFLR2_NodeDist_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64/CAPS/legacy/examples/regressionTest/pyCAPSlog.txt
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 = 4
Name = TunnelWall, index = 1
Name = OutFlow, index = 2
Name = InFlow, index = 3
Name = Airfoil, index = 4
Getting mesh sizing parameters
Mesh sizing name - 2DSlice
Mesh sizing name - Airfoil
Mesh sizing name - InFlow
Mesh sizing name - OutFlow
Mesh sizing name - TunnelWall
Done getting mesh sizing parameters
Getting 2D mesh for body 1 (of 1)
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.7
AFLR2 : Version Date 07/16/23 @ 01:42PM
AFLR2 : Compile OS Darwin 22.5.0 x86_64
AFLR2 : Compile Date 07/25/23 @ 11:59AM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR2 IC : INPUT DATA CHECK
AFLR2 IC : Nodes, Faces = 224 0
AFLR2 : CPU Time = 0.001 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 = 0.001 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 = 0.006 seconds
AFLR2 QI : QUALITY IMPROVEMENT
AFLR2 QI : Nodes, Faces = 3715 7206
AFLR2 : CPU Time = 0.002 seconds
AFLR2 : DONE
Writing AFLR3 file ....
Finished writing AFLR3 file
Number of nodes = 3715
Number of elements = 7430
Number of tris = 7206
Number of quad = 0
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
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.5.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2023, 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 73 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| 298| 1/3.52| 6.37252|
+-------------------------------------------+
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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 5.1814e-02| -0.385358| 2.453598| 1.625650| 5.369499| 0.360138|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.1230e-02| -0.512634| 2.087781| 1.374671| 4.973554| 1.183036|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.0223e-02| -0.792582| 1.733529| 1.142729| 4.657622| 3.896320|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 5.0346e-02| -0.880738| 1.486539| 1.023158| 4.334759| 14.592265|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 5.0326e-02| -0.987528| 1.351478| 0.932491| 4.191092| 111.166022|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 5.0244e-02| -1.104038| 1.188715| 0.874764| 3.951825| -483.924340|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 5.0263e-02| -1.178622| 1.124587| 0.844310| 3.820426| 127.331200|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 5.0300e-02| -1.243517| 1.097463| 0.824869| 3.768858| 40.162273|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 5.0417e-02| -1.287932| 1.075843| 0.810639| 3.733440| 25.154653|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 5.0474e-02| -1.300689| 1.046363| 0.775886| 3.684245| 21.097801|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.30069| < -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).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
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 = 0.650457 Cd = 0.030831
Cmz = 0.373226
Cx = 0.030831 Cy = 0.650457
Pressure Contribution
Cl_p = 0.650457 Cd_p = 0.030831
Cmz_p = 0.373226
Cx_p = 0.030831 Cy_p = 0.650457
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 0m2.419s
user 0m1.652s
sys 0m0.940s
+ 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 = 4
Name = TunnelWall, index = 1
Name = OutFlow, index = 2
Name = InFlow, index = 3
Name = Airfoil, index = 4
Getting mesh sizing parameters
Mesh sizing name - 2DSlice
Mesh sizing name - Airfoil
Mesh sizing name - InFlow
Mesh sizing name - OutFlow
Mesh sizing name - TunnelWall
Done getting mesh sizing parameters
Getting 2D mesh for body 1 (of 1)
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.7
AFLR2 : Version Date 07/16/23 @ 01:42PM
AFLR2 : Compile OS Darwin 22.5.0 x86_64
AFLR2 : Compile Date 07/25/23 @ 11:59AM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR2 IC : INPUT DATA CHECK
AFLR2 IC : Nodes, Faces = 545 0
AFLR2 : CPU Time = 0.000 seconds
AFLR2 EG : EDGE GRID RE-GENERATION
AFLR2 EG : Nodes, Edges = 545 545
AFLR2 : CPU Time = 0.000 seconds
AFLR2 IG : INITIAL GRID GENERATION
AFLR2 IG : Nodes, Faces = 0 2
AFLR2 IG : Nodes, Faces = 110 222
AFLR2 IG : Nodes, Faces = 220 442
AFLR2 IG : Nodes, Faces = 330 662
AFLR2 IG : Nodes, Faces = 440 882
AFLR2 IG : Nodes, Faces = 517 1036
AFLR2 IG : Nodes, Faces = 545 1092
AFLR2 IG : Nodes, Faces = 549 1092
AFLR2 IG : Nodes, Faces = 545 545
AFLR2 : CPU Time = 0.002 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 = 0.043 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 811
AFLR2 QI : Nodes, Faces = 11154 10476
AFLR2 QI : Nodes, Faces = 11154 21763
AFLR2 QI : Nodes, Faces = 11154 805
AFLR2 QI : Nodes, Faces = 11154 10479
AFLR2 QI : Nodes, Faces = 11154 21763
AFLR2 QI : Nodes, Faces = 11154 911
AFLR2 QI : Nodes, Faces = 11154 10426
AFLR2 QI : Nodes, Faces = 11154 21763
AFLR2 QI : Nodes, Faces = 11153 915
AFLR2 QI : Nodes, Faces = 11153 10423
AFLR2 QI : Nodes, Faces = 11153 917
AFLR2 QI : Nodes, Faces = 11153 10423
AFLR2 : CPU Time = 0.020 seconds
AFLR2 : DONE
EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)!
EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)!
EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)!
EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)!
Writing AFLR3 file ....
Finished writing AFLR3 file
Number of nodes = 11153
Number of elements = 11885
Number of tris = 917
Number of quad = 10423
Writing TECPLOT file: pyCAPS_su2_aflr2.dat ....
Finished writing TECPLOT file
EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)!
EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)!
EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)!
EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)!
EGADS Internal: Face 1, Side 11077 11153 complete [but 18248] (EG_makeConnect)!
EGADS Internal: Face 1, Side 10985 11077 complete [but 18248] (EG_makeConnect)!
EGADS Internal: Face 1, Side 10985 11152 complete [but 18249] (EG_makeConnect)!
EGADS Internal: Face 1, Side 11152 11153 complete [but 19022] (EG_makeConnect)!
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
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.5.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2023, 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.
11340 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).
917 triangles.
10423 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 917 TRIANGLE volume elements.
There has been a re-orientation of 10423 QUADRILATERAL volume elements.
There has been a re-orientation of 73 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 999.878.
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.)| 49.3184| 90|
| CV Face Area Aspect Ratio| 1.00035| 33.4982|
| CV Sub-Volume Ratio| 1.00001| 7.89914|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 11153| 1/1.00| 10|
| 1| 2702| 1/4.13| 7.38309|
| 2| 549| 1/4.92| 4.99198|
+-------------------------------------------+
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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 1.2037e-01| 0.071067| 2.739763| 1.616077| 5.599701| 0.055267|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.1859e-01| -0.447576| 2.193837| 1.571349| 5.070382| 0.046028|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.1898e-01| -0.561159| 2.074597| 1.490746| 4.953698| 0.033910|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.1864e-01| -0.723326| 1.921155| 1.390756| 4.790278| 0.049695|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.1863e-01| -0.876572| 1.825653| 1.275093| 4.637161| 0.133976|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.1876e-01| -1.029177| 1.759196| 1.156078| 4.482282| 0.368542|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.1802e-01| -1.215334| 1.704909| 1.114966| 4.286060| 0.974759|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.1745e-01| -1.329970| 1.644937| 1.145030| 4.116982| 2.716332|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.1739e-01| -1.270672| 1.570739| 1.155400| 4.139480| 16.569216|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.1775e-01| -1.221243| 1.499646| 1.130319| 4.189559| -6.277653|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.22124| < -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).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
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 = 0.072253 Cd = -0.01151
Cmz = 0.070975
Cx = -0.01151 Cy = 0.072253
Pressure Contribution
Cl_p = 0.072253 Cd_p = -0.01151
Cmz_p = 0.070975
Cx_p = -0.01151 Cy_p = 0.072253
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 0m3.643s
user 0m2.897s
sys 0m1.035s
+ 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.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
Getting volume mesh
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.7
AFLR2 : Version Date 07/16/23 @ 01:42PM
AFLR2 : Compile OS Darwin 22.5.0 x86_64
AFLR2 : Compile Date 07/25/23 @ 11:59AM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR4 : ---------------------------------------
AFLR4 : AFLR4 LIBRARY
AFLR4 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR4 : TRIA/QUAD SURFACE GRID GENERATOR
AFLR4 : Version Number 11.5.9
AFLR4 : Version Date 08/14/23 @ 12:27AM
AFLR4 : Compile OS Darwin 22.5.0 x86_64
AFLR4 : Compile Date 08/14/23 @ 01:13PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.25
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.25
EGADS : OpenCASCADE Version 7.6.0
EGADS : ---------------------------------------
Volume mesh:
Number of nodes = 77412
Number of elements = 451243
Number of triangles = 15676
Number of quadrilatarals = 0
Number of tetrahedrals = 435567
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 (7.5.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2023, 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.
77412 grid points.
435567 volume elements.
3 surface markers.
9898 boundary elements in index 0 (Marker = BC_1).
5358 boundary elements in index 1 (Marker = BC_2).
420 boundary elements in index 2 (Marker = BC_3).
435567 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: 2.08667e+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: 4873.1. Mean K: 51.0385. Standard deviation K: 239.256.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 45.7284| 87.0164|
| CV Face Area Aspect Ratio| 1.03673| 95.7539|
| CV Sub-Volume Ratio| 1.02813| 444.888|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 77412| 1/1.00| 10|
| 1| 12710| 1/6.09| 8.21367|
| 2| 1910| 1/6.65| 6.55025|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.90569 m.
Wetted area = 119.573 m^2.
Area projection in the x-plane = 11.2425 m^2, y-plane = 5.04269 m^2, z-plane = 56.272 m^2.
Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.583228 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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 3.1733e+00| -0.376640| 1.995904| 1.675175| 5.114255| 1.905661|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.0938e+00| -0.207195| 2.258301| 1.982708| 5.297198| 2.557734|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.0699e+00| -0.130327| 2.394724| 2.262373| 5.370499| 4.028292|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.0388e+00| -0.158666| 2.463906| 2.419760| 5.334413| 6.128930|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.0222e+00| -0.193503| 2.478507| 2.496803| 5.292294| 8.076759|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.193503| < -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).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
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 = 0.871122 Cd = 0.107855
Cmx = -0.000116 Cmy = -0.248846 Cmz = 4.7e-05
Cx = 0.092636 Cy = -7.7e-05 Cz = 0.872872
Pressure Contribution
Cl_p = 0.871122 Cd_p = 0.107855
Cmx_p = -0.000116 Cmy_p = -0.248846 Cmz_p = 4.7e-05
Cx_p = 0.092636 Cy_p = -7.7e-05 Cz_p = 0.872872
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 0m47.239s
user 0m38.602s
sys 0m2.085s
+ 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 (7.5.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2023, 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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 8.8396e-02| -1.163171| 1.073770| 1.341444| 4.312165| 0.062120|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 8.7375e-02| -1.561828| 0.808636| 0.967487| 3.922716| 0.139775|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 8.7547e-02| -1.601698| 0.943793| 1.009036| 3.876382| 0.373708|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 8.8113e-02| -1.659374| 1.008221| 1.015635| 3.799753| 0.952935|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 8.7610e-02| -1.663585| 1.011627| 0.956487| 3.788246| 2.344781|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 8.7892e-02| -1.633451| 0.991734| 0.872954| 3.829708| 6.259549|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 8.8374e-02| -1.626398| 0.990123| 0.847075| 3.843511| 26.349556|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 8.7768e-02| -1.643439| 1.009125| 0.895796| 3.825758| -56.104876|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 8.7189e-02| -1.659565| 1.020774| 0.939260| 3.804303| -24.431167|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 8.7161e-02| -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).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
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 0m3.095s
user 0m2.150s
sys 0m0.941s
+ 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 = 265
Number of elements = 526
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 526
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3137
Total number of elements = 6262
Writing TECPLOT file: egadsTessMesh_Surf_0.dat ....
Finished writing TECPLOT file
Writing TECPLOT file: egadsTessMesh_Surf_1.dat ....
Finished writing TECPLOT file
Writing TECPLOT file: egadsTessMesh_Surf_2.dat ....
Finished writing TECPLOT file
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Number of surface: nodes - 3137, elements - 6262
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds: 0.028289
Creating surface mesh ...
Surface mesh seconds: 0.007043
Recovering boundaries...
Boundary recovery seconds: 0.097536
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds: 0.00821
Suppressing Steiner points ...
Steiner suppression seconds: 2e-05
Recovering Delaunayness...
Delaunay recovery seconds: 0.013289
Refining mesh...
4186 insertions, added 2132 points, 130189 tetrahedra in queue.
1393 insertions, added 396 points, 133609 tetrahedra in queue.
1857 insertions, added 413 points, 131356 tetrahedra in queue.
2476 insertions, added 454 points, 112928 tetrahedra in queue.
3300 insertions, added 466 points, 67068 tetrahedra in queue.
4399 insertions, added 435 points, 292 tetrahedra in queue.
5864 insertions, added 590 points, 479 tetrahedra in queue.
Refinement seconds: 0.966731
Smoothing vertices...
Mesh smoothing seconds: 0.601847
Improving mesh...
Mesh improvement seconds: 0.014982
Jettisoning redundant points.
Writing nodes.
Writing elements.
Writing faces.
Writing edges.
Output seconds: 0.003334
Total running seconds: 1.74158
Statistics:
Input points: 3137
Input facets: 6262
Input segments: 9393
Input holes: 2
Input regions: 0
Mesh points: 8091
Mesh tetrahedra: 39789
Mesh faces: 82710
Mesh faces on exterior boundary: 6264
Mesh faces on input facets: 6264
Mesh edges on input segments: 9394
Steiner points on input segments: 1
Steiner points inside domain: 4953
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 (7.5.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2023, 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.
8091 grid points.
39789 volume elements.
3 surface markers.
4468 boundary elements in index 0 (Marker = BC_1).
1270 boundary elements in index 1 (Marker = BC_2).
526 boundary elements in index 2 (Marker = BC_3).
39789 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 2.08926e+06.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 414.134. Mean K: 30.5804. Standard deviation K: 37.5377.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 1.66644| 84.3027|
| CV Face Area Aspect Ratio| 1.51408| 6441.7|
| CV Sub-Volume Ratio| 1.03202| 58553.9|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 8091| 1/1.00| 10|
| 1| 1351| 1/5.99| 8.25992|
| 2| 223| 1/6.06| 6.79647|
+-------------------------------------------+
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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 2.6562e-01| 0.617984| 3.049944| 2.093190| 6.108879| 1.810742|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.6667e-01| 0.748911| 3.251769| 2.987153| 6.248586| 2.155825|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.6879e-01| 0.688623| 3.311837| 3.249508| 6.186781| 3.173369|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 2.6918e-01| 0.587426| 3.265724| 3.310895| 6.060983| 4.532123|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.6853e-01| 0.563655| 3.196458| 3.256149| 6.028232| 5.638253|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 0.563655| < -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).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
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 = 0.751804 Cd = 0.13334
Cmx = -0.004647 Cmy = -0.210652 Cmz = 0.001238
Cx = 0.120199 Cy = 0.000192 Cz = 0.754017
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: 'capsAnalysis.getAnalysisVal' 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 0m22.847s
user 0m18.498s
sys 0m0.940s
+ 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: 0.080313
Creating surface mesh ...
Surface mesh seconds: 0.027176
Recovering boundaries...
Warning: 6 segments are not recovered.
Boundary recovery seconds: 0.233423
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds: 0.0184
Suppressing Steiner points ...
Steiner suppression seconds: 2.6e-05
Recovering Delaunayness...
Delaunay recovery seconds: 0.032274
Refining mesh...
12618 insertions, added 5287 points, 2686 tetrahedra in queue.
Refinement seconds: 0.782399
Smoothing vertices...
Mesh smoothing seconds: 0.719044
Improving mesh...
Mesh improvement seconds: 0.0262
Jettisoning redundant points.
Writing nodes.
Writing elements.
Writing faces.
Writing edges.
Output seconds: 0.008524
Total running seconds: 1.93361
Statistics:
Input points: 9462
Input facets: 18920
Input segments: 28380
Input holes: 1
Input regions: 0
Mesh points: 14838
Mesh tetrahedra: 61174
Mesh faces: 131811
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: 5373
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 (7.5.1) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 8.0.0 "Harrier" |
| \__ \ |_| |/ / |
| |___/\___//___| 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 2012-2023, 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.
14838 grid points.
61174 volume elements.
2 surface markers.
7622 boundary elements in index 0 (Marker = BC_1).
11304 boundary elements in index 1 (Marker = BC_2).
61174 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: 0.525156. Standard deviation K: 2.5799.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 1.95659| 83.8221|
| CV Face Area Aspect Ratio| 1.41663| 23894.3|
| CV Sub-Volume Ratio| 1| 751631|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 14838| 1/1.00| 10|
| 1| 2667| 1/5.56| 8.46526|
| 2| 482| 1/5.53| 7.17915|
+-------------------------------------------+
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
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
WARNING: SU2 was not compiled for an AVX-capable architecture. Performance could be better,
see https://su2code.github.io/docs_v7/Build-SU2-Linux-MacOS/#compiler-optimizations
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 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| 5.2270e-01| 2.731555| 5.665595| 4.729268| 8.731031| -0.388627|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 5.0481e-01| 3.124663| 6.168534| 5.652640| 9.147040| -0.130921|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 5.0672e-01| 3.268952| 6.335622| 5.772165| 9.248809| -0.048395|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 5.0372e-01| 3.301113| 6.357856| 5.754955| 9.278436| -0.050401|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 5.0336e-01| 3.246860| 6.294604| 5.587733| 9.212152| -0.079853|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 3.24686| < -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 127 non-physical points in the solution.
Warning: 84 reconstructed states for upwinding are non-physical.
--------------------------- Finalizing Solver ---------------------------
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 = -9.174312 Cd = 114.890297
Cmx = -22.490238 Cmy = 9469.942794 Cmz = 370.964066
Cx = 115.21299 Cy = 3.225665 Cz = -3.148845
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 0m14.830s
user 0m14.433s
sys 0m1.614s
+ 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 0.11228138
C_Y 0.0048773075
C_N -0.00061621474
C_D 0.11219148
C_S 0.0048773075
C_L -0.004534403
C_l 0.000749624
C_m 0.00023379
C_n 0.244516
C_M_x 0.00928265
C_M_y 0.00023379
C_M_z 0.244341
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 3m32.939s
user 4m19.637s
sys 0m2.709s
+ 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] 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] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64')
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Successfully parsed console log
[Static Analysis] -> found 0 issues (skipped 0 duplicates)
[Static Analysis] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_RegCaps/7.6/CAPS/CFD/DARWIN64')
[Static Analysis] Skipping post processing
[Static Analysis] No filter has been set, publishing all 0 issues
[Static Analysis] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] No valid reference build found
[Static Analysis] All reported issues will be considered outstanding
[Static Analysis] No quality gates have been set - skipping
[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 #619'.
[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
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