CAPS verification (using c-executables) case ./fun3dAFLR2Test passed (as expected)
=============================================
=================================================
+ echo './fun3dTetgenTest test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/cCAPSlog.txt
./fun3dTetgenTest test;
+ ./fun3dTetgenTest 0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/cCAPSlog.txt
Attention: fun3dTetgenTest is hard coded to look for ../csmData/cfdMultiBody.csm
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 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 = 9607
Number of elements = 19210
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 19210
Number of quadrilateral elements = 0
Body 2 (of 3)
Number of nodes = 6142
Number of elements = 12280
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 12280
Number of quadrilateral elements = 0
Body 3 (of 3)
Number of nodes = 265
Number of elements = 526
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 526
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 16014
Total number of elements = 32016
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Number of surface: nodes - 16014, elements - 32016
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds: 0.850183
Creating surface mesh ...
Surface mesh seconds: 0.196361
Recovering boundaries...
Boundary recovery seconds: 0.342306
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds: 0.174024
Recovering Delaunayness...
Delaunay recovery seconds: 0.188598
Refining mesh...
21346 insertions, added 17000 points, 773281 tetrahedra in queue.
7108 insertions, added 2714 points, 325605 tetrahedra in queue.
Refinement seconds: 7.80951
Smoothing vertices...
Mesh smoothing seconds: 9.7804
Improving mesh...
Mesh improvement seconds: 0.709007
Writing nodes.
Writing elements.
Writing faces.
Writing edges.
Output seconds: 0.073979
Total running seconds: 20.1322
Statistics:
Input points: 16014
Input facets: 32016
Input segments: 48024
Input holes: 2
Input regions: 0
Mesh points: 37066
Mesh tetrahedra: 178778
Mesh faces: 373564
Mesh faces on exterior boundary: 32016
Mesh faces on input facets: 32016
Mesh edges on input segments: 48024
Steiner points inside domain: 21052
Done meshing using TetGen!
Getting CFD boundary conditions
Boundary condition name - Wing1
Boundary condition name - Wing2
Boundary condition name - Farfield
Done getting CFD boundary conditions
Python library was linked, but will not be used!
Writing MAPBC file ....
Finished writing MAPBC file
Warning: The fun3d.nml file will be overwritten!
Writing fun3d.nml
Info: No recognized data transfer names found.
NOT Running fun3d!
real 0m50.907s
user 0m59.467s
sys 0m0.443s
+ status=0
+ set +x
=============================================
CAPS verification (using c-executables) case ./fun3dTetgenTest passed (as expected)
=============================================
All tests pass!
=================================================
=================================================
++ '[' '!' -z '-L/Users/jenkins/util/ESP/Python/ESP_Python-3.9.13/lib -lpython3.9 -ldl -framework CoreFoundation' ']'
++ ./execute_PyTestRegression.sh CFD
=================================================
Using python : /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/bin/python
=================================================
Running.... CFD PyTests
=================================================
+ echo 'su2_and_AFLR2_NodeDist_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_and_AFLR2_NodeDist_PyTest.py test;
+ python -u su2_and_AFLR2_NodeDist_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 5
Name = 2DSlice, index = 1
Name = TunnelWall, index = 2
Name = OutFlow, index = 3
Name = InFlow, index = 4
Name = Airfoil, index = 5
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 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 9.14.6
AFLR2 : Version Date 11/20/22 @ 09:21PM
AFLR2 : Compile OS Darwin 22.3.0 arm64
AFLR2 : Compile Date 02/27/23 @ 03:36PM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR2 IC : INPUT DATA CHECK
AFLR2 IC : Nodes, Faces = 224 0
AFLR2 : CPU Time = 0.000 seconds
AFLR2 EG : EDGE GRID RE-GENERATION
AFLR2 EG : Nodes, Edges = 224 224
AFLR2 : CPU Time = 0.000 seconds
AFLR2 IG : INITIAL GRID GENERATION
AFLR2 IG : Nodes, Faces = 0 2
AFLR2 IG : Nodes, Faces = 46 94
AFLR2 IG : Nodes, Faces = 92 186
AFLR2 IG : Nodes, Faces = 138 278
AFLR2 IG : Nodes, Faces = 184 370
AFLR2 IG : Nodes, Faces = 196 394
AFLR2 IG : Nodes, Faces = 224 450
AFLR2 IG : Nodes, Faces = 228 450
AFLR2 IG : Nodes, Faces = 224 224
AFLR2 : CPU Time = 0.000 seconds
AFLR2 GG : FIELD GRID GENERATION
AFLR2 GG : Nodes, Faces = 224 224
AFLR2 GG : Nodes, Faces = 440 656
AFLR2 GG : Nodes, Faces = 649 1074
AFLR2 GG : Nodes, Faces = 853 1482
AFLR2 GG : Nodes, Faces = 1050 1876
AFLR2 GG : Nodes, Faces = 1238 2252
AFLR2 GG : Nodes, Faces = 1421 2618
AFLR2 GG : Nodes, Faces = 1594 2964
AFLR2 GG : Nodes, Faces = 1760 3296
AFLR2 GG : Nodes, Faces = 1915 3606
AFLR2 GG : Nodes, Faces = 2063 3902
AFLR2 GG : Nodes, Faces = 2202 4180
AFLR2 GG : Nodes, Faces = 2314 4404
AFLR2 GG : Nodes, Faces = 2423 4622
AFLR2 GG : Nodes, Faces = 2528 4832
AFLR2 GG : Nodes, Faces = 2634 5044
AFLR2 GG : Nodes, Faces = 2732 5240
AFLR2 GG : Nodes, Faces = 2831 5438
AFLR2 GG : Nodes, Faces = 2927 5630
AFLR2 GG : Nodes, Faces = 3018 5812
AFLR2 GG : Nodes, Faces = 3109 5994
AFLR2 GG : Nodes, Faces = 3202 6180
AFLR2 GG : Nodes, Faces = 3295 6366
AFLR2 GG : Nodes, Faces = 3386 6548
AFLR2 GG : Nodes, Faces = 3464 6704
AFLR2 GG : Nodes, Faces = 3535 6846
AFLR2 GG : Nodes, Faces = 3594 6964
AFLR2 GG : Nodes, Faces = 3639 7054
AFLR2 GG : Nodes, Faces = 3671 7118
AFLR2 GG : Nodes, Faces = 3691 7158
AFLR2 GG : Nodes, Faces = 3705 7186
AFLR2 GG : Nodes, Faces = 3712 7200
AFLR2 GG : Nodes, Faces = 3715 7206
AFLR2 : CPU Time = 0.004 seconds
AFLR2 QI : QUALITY IMPROVEMENT
AFLR2 QI : Nodes, Faces = 3715 7206
AFLR2 : CPU Time = 0.000 seconds
AFLR2 : DONE
UG_IO : OUTPUT GRID
UG_IO : Writing Data
UG_IO : Grid File Name = /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/SU2AFLR2NodeDistAnalysisTest/Scratch/aflr2/aflr2.lb8.ugrid
UG_IO : Boundary Edges = 224
UG_IO : Nodes = 3715
UG_IO : Quad Faces = 0
UG_IO : Tria Faces = 7206
UG_IO : CPU Time = 0.001 seconds
Number of nodes = 3715
Number of elements = 7430
Number of tris = 7206
Number of quad = 0
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Airfoil
Boundary condition name - InFlow
Boundary condition name - OutFlow
Boundary condition name - TunnelWall
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.4.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_5.
Surface(s) plotted in the output file: BC_5, BC_2.
Input mesh file name: ../aflr2/aflr2.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 10.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| TECPLOT| 250|
| SURFACE_TECPLOT| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_pyCAPS_SU2_aflr2.dat.
Surface file name: surface_flow_pyCAPS_SU2_aflr2.
Volume file name: flow_pyCAPS_SU2_aflr2.
Restart file name: restart_flow_pyCAPS_SU2_aflr2.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_5|
| | BC_2|
+-----------------------------------------------------------------------+
| Inlet boundary| BC_4|
+-----------------------------------------------------------------------+
| Outlet boundary| BC_3|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Two dimensional problem.
3715 grid points.
7206 volume elements.
4 surface markers.
98 boundary elements in index 0 (Marker = BC_2).
24 boundary elements in index 1 (Marker = BC_3).
24 boundary elements in index 2 (Marker = BC_4).
78 boundary elements in index 3 (Marker = BC_5).
7206 triangles.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
There has been a re-orientation of 7206 TRIANGLE volume elements.
There has been a re-orientation of 224 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 999.917.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 177.06. Mean K: 1.97232. Standard deviation K: 13.0434.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 63.4343| 90|
| CV Face Area Aspect Ratio| 1| 5.23543|
| CV Sub-Volume Ratio| 1| 3.11804|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 3715| 1/1.00| 10|
| 1| 1048| 1/3.54| 7.96696|
| 2| 299| 1/3.51| 6.3832|
+-------------------------------------------+
Finding max control volume width.
Wetted area = 2.06136 m.
Area projection in the x-plane = 0.178383 m, y-plane = 0.994925 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.138389 m.
Min. coordinate in the x-direction = -0.000250564 m, y-direction = -0.0152 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_5 is NOT a single straight.
Boundary marker BC_2 is NOT a single straight.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 216054| 1| m^2/s^2| 216054|
| Velocity-X| 136.119| 1| m/s| 136.119|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity Magnitude| 136.119| 1| m/s| 136.119|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.4|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 2.7008e-02| -0.385358| 2.453598| 1.625650| 5.369499| 0.360386|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.6526e-02| -0.521485| 2.079409| 1.371893| 4.965390| 1.182869|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.7212e-02| -0.795894| 1.733901| 1.139977| 4.664635| 3.893206|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.6612e-02| -0.885699| 1.481333| 1.013745| 4.332779| 14.565626|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.7181e-02| -0.993750| 1.340252| 0.917512| 4.182929| 110.245147|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 3.6415e-02| -1.110400| 1.172200| 0.857005| 3.936064| -495.837992|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 3.4839e-02| -1.185766| 1.111335| 0.833878| 3.815560| 126.876277|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 3.6680e-02| -1.253010| 1.087204| 0.820499| 3.761995| 40.129370|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 3.7564e-02| -1.297506| 1.067370| 0.803440| 3.702559| 25.133461|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 3.8010e-02| -1.307387| 1.040693| 0.767965| 3.668428| 21.072343|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.30739| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_pyCAPS_SU2_aflr2.dat |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat).
|CSV file |surface_flow_pyCAPS_SU2_aflr2.csv |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat).
|Tecplot binary |flow_pyCAPS_SU2_aflr2.szplt |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat).
|Tecplot binary surface |surface_flow_pyCAPS_SU2_aflr2.szplt|
Error in tecFileWriterClose: Not all node map values for zone 1 have been written.
Currently need 352 more values.0: Error finishing Tecplot file output.
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_aflr2.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.650422 Cd = 0.030866
Cmz = 0.373254
Cx = 0.030866 Cy = 0.650422
Pressure Contribution
Cl_p = 0.650422 Cd_p = 0.030866
Cmz_p = 0.373254
Cx_p = 0.030866 Cy_p = 0.650422
Viscous Contribution
Cl_v = 0.0 Cd_v = 0.0
Cmz_v = 0.0
Cx_v = 0.0 Cy_v = 0.0
real 0m2.661s
user 0m1.951s
sys 0m0.462s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_and_AFLR2_NodeDist_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'su2_and_AFLR2_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_and_AFLR2_PyTest.py test;
+ python -u su2_and_AFLR2_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Saving geometry
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 5
Name = 2DSlice, index = 1
Name = TunnelWall, index = 2
Name = OutFlow, index = 3
Name = InFlow, index = 4
Name = Airfoil, index = 5
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 4
Name = TunnelWall, index = 1
Name = OutFlow, index = 2
Name = InFlow, index = 3
Name = Airfoil, index = 4
Getting mesh sizing parameters
Mesh sizing name - 2DSlice
Mesh sizing name - Airfoil
Mesh sizing name - InFlow
Mesh sizing name - OutFlow
Mesh sizing name - TunnelWall
Done getting mesh sizing parameters
Getting 2D mesh for body 1 (of 1)
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.6
AFLR2 : Version Date 11/20/22 @ 09:21PM
AFLR2 : Compile OS Darwin 22.3.0 arm64
AFLR2 : Compile Date 02/27/23 @ 03:36PM
AFLR2 : Copyright 1994-2021, D.L. Marcum
AFLR2 : ---------------------------------------
AFLR2 IC : INPUT DATA CHECK
AFLR2 IC : Nodes, Faces = 545 0
AFLR2 : CPU Time = 0.000 seconds
AFLR2 EG : EDGE GRID RE-GENERATION
AFLR2 EG : Nodes, Edges = 545 545
AFLR2 : CPU Time = 0.000 seconds
AFLR2 IG : INITIAL GRID GENERATION
AFLR2 IG : Nodes, Faces = 0 2
AFLR2 IG : Nodes, Faces = 110 222
AFLR2 IG : Nodes, Faces = 220 442
AFLR2 IG : Nodes, Faces = 330 662
AFLR2 IG : Nodes, Faces = 440 882
AFLR2 IG : Nodes, Faces = 517 1036
AFLR2 IG : Nodes, Faces = 545 1092
AFLR2 IG : Nodes, Faces = 549 1092
AFLR2 IG : Nodes, Faces = 545 545
AFLR2 : CPU Time = 0.001 seconds
AFLR2 GG : FIELD GRID GENERATION
AFLR2 GGp: Nodes, Faces = 545 545
AFLR2 GGp: Nodes, Faces = 1083 1621
AFLR2 GGp: Nodes, Faces = 1616 2687
AFLR2 GGp: Nodes, Faces = 2144 3743
AFLR2 GGp: Nodes, Faces = 2661 4777
AFLR2 GGp: Nodes, Faces = 3171 5797
AFLR2 GGp: Nodes, Faces = 3672 6799
AFLR2 GGp: Nodes, Faces = 4158 7771
AFLR2 GGp: Nodes, Faces = 4653 8761
AFLR2 GGp: Nodes, Faces = 5142 9739
AFLR2 GGp: Nodes, Faces = 5608 10671
AFLR2 GGp: Nodes, Faces = 6055 11565
AFLR2 GGp: Nodes, Faces = 6482 12419
AFLR2 GGp: Nodes, Faces = 6880 13215
AFLR2 GGp: Nodes, Faces = 7257 13969
AFLR2 GGp: Nodes, Faces = 7614 14683
AFLR2 GGp: Nodes, Faces = 7947 15349
AFLR2 GGp: Nodes, Faces = 8276 16007
AFLR2 GGp: Nodes, Faces = 8575 16605
AFLR2 GGp: Nodes, Faces = 8869 17193
AFLR2 GGp: Nodes, Faces = 9140 17735
AFLR2 GGp: Nodes, Faces = 9401 18257
AFLR2 GGp: Nodes, Faces = 9654 18763
AFLR2 GGp: Nodes, Faces = 9887 19229
AFLR2 GGp: Nodes, Faces = 10110 19675
AFLR2 GGp: Nodes, Faces = 10315 20085
AFLR2 GGp: Nodes, Faces = 10497 20449
AFLR2 GGp: Nodes, Faces = 10656 20767
AFLR2 GGp: Nodes, Faces = 10791 21037
AFLR2 GGp: Nodes, Faces = 10919 21293
AFLR2 GGp: Nodes, Faces = 11022 21499
AFLR2 GGp: Nodes, Faces = 11092 21639
AFLR2 GGp: Nodes, Faces = 11145 21745
AFLR2 GGp: Nodes, Faces = 11156 21767
AFLR2 : CPU Time = 0.027 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 = 0.008 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)!
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
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Airfoil
Boundary condition name - InFlow
Boundary condition name - OutFlow
Boundary condition name - TunnelWall
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.4.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_5.
Surface(s) plotted in the output file: BC_5, BC_2.
Input mesh file name: ../aflr2/aflr2.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 10.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| TECPLOT| 250|
| SURFACE_TECPLOT| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_pyCAPS_su2_aflr2.dat.
Surface file name: surface_flow_pyCAPS_su2_aflr2.
Volume file name: flow_pyCAPS_su2_aflr2.
Restart file name: restart_flow_pyCAPS_su2_aflr2.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_5|
| | BC_2|
+-----------------------------------------------------------------------+
| Inlet boundary| BC_4|
+-----------------------------------------------------------------------+
| Outlet boundary| BC_3|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Two dimensional problem.
11153 grid points.
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 545 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| 552| 1/4.89| 5.0056|
+-------------------------------------------+
Finding max control volume width.
Wetted area = 2.06265 m.
Area projection in the x-plane = 0.211192 m, y-plane = 0.997011 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.102037 m.
Min. coordinate in the x-direction = 0.000323229 m, y-direction = -0.108492 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_5 is NOT a single straight.
Boundary marker BC_2 is NOT a single straight.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 216054| 1| m^2/s^2| 216054|
| Velocity-X| 136.119| 1| m/s| 136.119|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity Magnitude| 136.119| 1| m/s| 136.119|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.4|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.0736e-01| 0.071067| 2.739763| 1.616077| 5.599701| 0.056234|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.0209e-01| -0.451613| 2.192234| 1.565785| 5.066972| 0.050900|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.0094e-01| -0.564854| 2.070558| 1.491520| 4.949788| 0.047848|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 9.9074e-02| -0.725300| 1.921765| 1.389268| 4.788747| 0.077818|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 9.9046e-02| -0.880808| 1.824143| 1.269532| 4.633030| 0.179832|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 9.9099e-02| -1.034651| 1.757534| 1.156825| 4.476500| 0.433263|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 9.8342e-02| -1.217617| 1.704018| 1.116027| 4.283168| 1.048119|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 9.9313e-02| -1.321693| 1.644061| 1.144142| 4.127043| 2.709048|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 9.9513e-02| -1.268757| 1.569895| 1.157468| 4.142893| 13.756362|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.0156e-01| -1.220113| 1.498009| 1.133292| 4.191258| -6.205456|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.22011| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_pyCAPS_su2_aflr2.dat |
Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat).
|CSV file |surface_flow_pyCAPS_su2_aflr2.csv |
Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat).
|Tecplot binary |flow_pyCAPS_su2_aflr2.szplt |
Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat).
|Tecplot binary surface |surface_flow_pyCAPS_su2_aflr2.szplt|
Error in tecFileWriterClose: Not all node map values for zone 1 have been written.
Currently need 994 more values.0: Error finishing Tecplot file output.
Writing the forces breakdown file (forces_breakdown_pyCAPS_su2_aflr2.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.064255 Cd = -0.010355
Cmz = 0.067884
Cx = -0.010355 Cy = 0.064255
Pressure Contribution
Cl_p = 0.064255 Cd_p = -0.010355
Cmz_p = 0.067884
Cx_p = -0.010355 Cy_p = 0.064255
Viscous Contribution
Cl_v = 0.0 Cd_v = 0.0
Cmz_v = 0.0
Cx_v = 0.0 Cy_v = 0.0
real 0m3.504s
user 0m3.478s
sys 0m0.291s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_and_AFLR2_PyTest.py passed (as expected)
=================================================
=================================================
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
+ echo 'su2_and_AFLR4_AFLR3_PyTest.py test;'
su2_and_AFLR4_AFLR3_PyTest.py test;
+ python -u su2_and_AFLR4_AFLR3_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
AFLR4 : Proximity BG Surface Grid Generation Skipped
AFLR4 : No Modifications Required
Warning: No capsGroup/capsIgnore attribute found on edge 1 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 2 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 3 of face 1, unable to assign a boundary index value
Warning: No capsGroup/capsIgnore attribute found on edge 4 of face 1, unable to assign a boundary index value
Writing TECPLOT file: AFLR4_Mesh.dat ....
Finished writing TECPLOT file
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 4
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Wake, index = 3
Name = Farfield, index = 4
Getting volume mesh
AFLR2 : ---------------------------------------
AFLR2 : AFLR2 LIBRARY
AFLR2 : ADVANCING-FRONT/LOCAL-RECONNECTION
AFLR2 : TRIA/QUAD GRID GENERATOR
AFLR2 : Version Number 9.14.6
AFLR2 : Version Date 11/20/22 @ 09:21PM
AFLR2 : Compile OS Darwin 22.3.0 arm64
AFLR2 : Compile Date 02/27/23 @ 03:36PM
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 11.3.17
AFLR4 : Version Date 03/03/23 @ 03:12PM
AFLR4 : Compile OS Darwin 22.3.0 arm64
AFLR4 : Compile Date 03/03/23 @ 03:13PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.23
EGADS : OpenCASCADE Version 7.4.1
EGADS : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.23
EGADS : OpenCASCADE Version 7.4.1
EGADS : ---------------------------------------
Volume mesh:
Number of nodes = 40106
Number of elements = 231493
Number of triangles = 12446
Number of quadrilatarals = 0
Number of tetrahedrals = 219047
Number of pyramids = 0
Number of prisms = 0
Number of hexahedrals = 0
Writing TECPLOT file: AFLR3_Mesh.dat ....
Finished writing TECPLOT file
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wake
Boundary condition name - Wing1
Boundary condition name - Wing2
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.5901.
Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 50 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 15.8114 m.
Surface(s) where the force coefficients are evaluated and
their reference origin for moment computation:
- BC_1 (0, 0, 0).
- BC_2 (0, 0, 0) m.
Surface(s) plotted in the output file: BC_1, BC_2.
Input mesh file name: ../aflr3/aflr3_0.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 10.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-8.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| PARAVIEW| 250|
| SURFACE_PARAVIEW| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_su2AFLRTest.dat.
Surface file name: surface_flow_su2AFLRTest.
Volume file name: flow_su2AFLRTest.
Restart file name: restart_flow_su2AFLRTest.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
| | BC_2|
+-----------------------------------------------------------------------+
| Far-field| BC_4|
+-----------------------------------------------------------------------+
| Internal boundary| BC_3|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
40106 grid points.
219047 volume elements.
4 surface markers.
6594 boundary elements in index 0 (Marker = BC_1).
5358 boundary elements in index 1 (Marker = BC_2).
74 boundary elements in index 2 (Marker = BC_3).
420 boundary elements in index 3 (Marker = BC_4).
219047 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: 61.8668. Standard deviation K: 266.942.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 19.4002| 84.2743|
| CV Face Area Aspect Ratio| 1.11297| 22794.1|
| CV Sub-Volume Ratio| 1.03791| 323406|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 40106| 1/1.00| 10|
| 1| 6579| 1/6.1| 8.21123|
| 2| 1031| 1/6.38| 6.64047|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.90569 m.
Wetted area = 118.035 m^2.
Area projection in the x-plane = 11.1422 m^2, y-plane = 4.96703 m^2, z-plane = 55.4177 m^2.
Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.582636 m.
Min. coordinate in the x-direction = 0 m, y-direction = -7.90569 m, z-direction = -0.41192 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Boundary marker BC_2 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 226952| 1| m^2/s^2| 226952|
| Velocity-X| 200.779| 1| m/s| 200.779|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 3.50461| 1| m/s| 3.50461|
| Velocity Magnitude| 200.809| 1| m/s| 200.809|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.5901|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.1423e+00| -0.068917| 2.293323| 2.029016| 5.421978| 1.969146|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 1.1691e+00| -0.039315| 2.438299| 2.155039| 5.458848| 2.667937|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 1.1532e+00| 0.007948| 2.550133| 2.398011| 5.504215| 4.074496|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 1.1572e+00| -0.030652| 2.599575| 2.535779| 5.459451| 6.009099|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 1.1672e+00| -0.079846| 2.606644| 2.589425| 5.407223| 7.708472|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 1.1661e+00| -0.091591| 2.594064| 2.603542| 5.403677| 8.911754|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 1.1617e+00| -0.100566| 2.554136| 2.607537| 5.395466| 9.751694|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 1.1608e+00| -0.131653| 2.491918| 2.604156| 5.355684| 10.227571|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 1.1591e+00| -0.179635| 2.431915| 2.587606| 5.295934| 10.320451|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 1.1590e+00| -0.220634| 2.402874| 2.546473| 5.253378| 10.117312|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -0.220634| < -8| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_su2AFLRTest.dat |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|CSV file |surface_flow_su2AFLRTest.csv |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview |flow_su2AFLRTest.vtu |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
|Paraview surface |surface_flow_su2AFLRTest.vtu |
Writing the forces breakdown file (forces_breakdown_su2AFLRTest.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.795115 Cd = 0.07859
Cmx = -0.000197 Cmy = -0.202378 Cmz = -0.000267
Cx = 0.064701 Cy = -0.000139 Cz = 0.796365
Pressure Contribution
Cl_p = 0.795115 Cd_p = 0.07859
Cmx_p = -0.000197 Cmy_p = -0.202378 Cmz_p = -0.000267
Cx_p = 0.064701 Cy_p = -0.000139 Cz_p = 0.796365
Viscous Contribution
Cl_v = 0.0 Cd_v = 0.0
Cmx_v = 0.0 Cmy_v = 0.0 Cmz_v = 0.0
Cx_v = 0.0 Cy_v = 0.0 Cz_v = 0.0
real 0m42.255s
user 0m31.331s
sys 0m0.681s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_and_AFLR4_AFLR3_PyTest.py passed (as expected)
=================================================
delaundo: /Users/jenkins/util/delaundo/delaundo/src/delaundo
=================================================
+ echo 'su2_and_Delaundo_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_and_Delaundo_PyTest.py test;
+ python -u su2_and_Delaundo_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 5
Name = 2DSlice, index = 1
Name = TunnelWall, index = 2
Name = OutFlow, index = 3
Name = InFlow, index = 4
Name = Airfoil, index = 5
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 5
Name = 2DSlice, index = 1
Name = TunnelWall, index = 2
Name = OutFlow, index = 3
Name = InFlow, index = 4
Name = Airfoil, index = 5
Getting mesh sizing parameters
Mesh sizing name - 2DSlice
Mesh sizing name - Airfoil
Mesh sizing name - InFlow
Mesh sizing name - OutFlow
Mesh sizing name - TunnelWall
Done getting mesh sizing parameters
Getting edge discretization for body 1
Delaundo expects 2D meshes be in the x-y plane... attempting to rotate mesh through node swapping!
Swapping z and y coordinates!
Writing delaundo control file - delaundo.ctr
Writing out *.pts file
Reading delaundo mesh file - delaundoMesh.mesh
Swapping y and z coordinates!
Writing TECPLOT file: delaundoMesh.dat ....
Finished writing TECPLOT file
Writing SU2 file ....
SU2 expects 2D meshes be in the x-y plane... attempting to rotate mesh!
Swapping z and y coordinates!
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Airfoil
Boundary condition name - InFlow
Boundary condition name - OutFlow
Boundary condition name - TunnelWall
Warning: No boundary condition specified for capsGroup 2DSlice!
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.4.
Angle of attack (AoA): 0 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_5.
Surface(s) plotted in the output file: BC_5, BC_2.
Input mesh file name: ../delaundo/delaundoMesh.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 10.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| TECPLOT| 250|
| SURFACE_TECPLOT| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_delaundoMesh.dat.
Surface file name: surface_flow_delaundoMesh.
Volume file name: flow_delaundoMesh.
Restart file name: restart_flow_delaundoMesh.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_5|
| | BC_2|
+-----------------------------------------------------------------------+
| Inlet boundary| BC_4|
+-----------------------------------------------------------------------+
| Outlet boundary| BC_3|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Two dimensional problem.
6335 grid points.
12376 volume elements.
5 surface markers.
24 boundary elements in index 0 (Marker = BC_2).
24 boundary elements in index 1 (Marker = BC_3).
24 boundary elements in index 2 (Marker = BC_2).
24 boundary elements in index 3 (Marker = BC_4).
198 boundary elements in index 4 (Marker = BC_5).
12376 triangles.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
There has been a re-orientation of 294 LINE surface elements.
Identifying edges and vertices.
Setting the control volume structure.
Area of the computational grid: 999.917.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 1792.95. Mean K: 10.8141. Standard deviation K: 104.33.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 45.3524| 89.2457|
| CV Face Area Aspect Ratio| 1.03245| 15.7098|
| CV Sub-Volume Ratio| 1| 7.93642|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 6335| 1/1.00| 10|
| 1| 1815| 1/3.49| 8.0289|
| 2| 519| 1/3.5| 6.4401|
+-------------------------------------------+
Finding max control volume width.
Wetted area = 2.07206 m.
Area projection in the x-plane = 0.179342 m, y-plane = 1.00053 m.
Max. coordinate in the x-direction = 1 m, y-direction = 0.138492 m.
Min. coordinate in the x-direction = -0.00104577 m, y-direction = -0.0151891 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_5 is NOT a single straight.
Boundary marker BC_2 is a single straight.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 216054| 1| m^2/s^2| 216054|
| Velocity-X| 136.119| 1| m/s| 136.119|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity Magnitude| 136.119| 1| m/s| 136.119|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.4|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 6.3945e-02| -1.163686| 1.073255| 1.340929| 4.311650| 0.061671|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 6.8563e-02| -1.568377| 0.814909| 0.963677| 3.916705| 0.144353|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 6.5435e-02| -1.613815| 0.940123| 1.014538| 3.865902| 0.383098|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 6.5312e-02| -1.678204| 0.986567| 1.029402| 3.782002| 0.970161|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 6.4961e-02| -1.673240| 0.982512| 0.972025| 3.776795| 2.379908|
| 0| 0| 5| 0.0000e+00| 0.0000e+00| 6.4504e-02| -1.632262| 0.968047| 0.868654| 3.827903| 6.320909|
| 0| 0| 6| 0.0000e+00| 0.0000e+00| 6.5437e-02| -1.626018| 0.975724| 0.835054| 3.842259| 25.935722|
| 0| 0| 7| 0.0000e+00| 0.0000e+00| 6.5506e-02| -1.650839| 1.000183| 0.890573| 3.818757| -60.978870|
| 0| 0| 8| 0.0000e+00| 0.0000e+00| 6.6005e-02| -1.679741| 1.014343| 0.938142| 3.785304| -25.297357|
| 0| 0| 9| 0.0000e+00| 0.0000e+00| 6.6367e-02| -1.692890| 1.005186| 0.937842| 3.767062| -21.973132|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 10) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| -1.69289| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_delaundoMesh.dat |
Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
|CSV file |surface_flow_delaundoMesh.csv |
Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
|Tecplot binary |flow_delaundoMesh.szplt |
Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
|Tecplot binary surface |surface_flow_delaundoMesh.szplt |
Error in tecFileWriterClose: Not all node map values for zone 1 have been written.
Currently need 492 more values.0: Error finishing Tecplot file output.
Writing the forces breakdown file (forces_breakdown_delaundoMesh.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.798939 Cd = -0.03636
Cmz = 0.411603
Cx = -0.03636 Cy = 0.798939
Pressure Contribution
Cl_p = 0.798939 Cd_p = -0.03636
Cmz_p = 0.411603
Cx_p = -0.03636 Cy_p = 0.798939
Viscous Contribution
Cl_v = 0.0 Cd_v = 0.0
Cmz_v = 0.0
Cx_v = 0.0 Cy_v = 0.0
real 0m2.244s
user 0m1.912s
sys 0m0.312s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_and_Delaundo_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'su2_and_Tetgen_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_and_Tetgen_PyTest.py test;
+ python -u su2_and_Tetgen_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Getting surface mesh for body 1 (of 3)
Getting surface mesh for body 2 (of 3)
Getting surface mesh for body 3 (of 3)
Body 1 (of 3)
Number of nodes = 2236
Number of elements = 4468
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 4468
Number of quadrilateral elements = 0
Body 2 (of 3)
Number of nodes = 636
Number of elements = 1268
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 1268
Number of quadrilateral elements = 0
Body 3 (of 3)
Number of nodes = 265
Number of elements = 526
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 526
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 3137
Total number of elements = 6262
Writing TECPLOT file: egadsTessMesh_Surf_0.dat ....
Finished writing TECPLOT file
Writing TECPLOT file: egadsTessMesh_Surf_1.dat ....
Finished writing TECPLOT file
Writing TECPLOT file: egadsTessMesh_Surf_2.dat ....
Finished writing TECPLOT file
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Number of surface: nodes - 3137, elements - 6262
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds: 0.114935
Creating surface mesh ...
Surface mesh seconds: 0.027517
Recovering boundaries...
Boundary recovery seconds: 0.229235
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds: 0.03258
Suppressing Steiner points ...
Steiner suppression seconds: 9e-06
Recovering Delaunayness...
Delaunay recovery seconds: 0.049465
Refining mesh...
4186 insertions, added 2159 points, 126369 tetrahedra in queue.
1393 insertions, added 415 points, 129993 tetrahedra in queue.
1857 insertions, added 443 points, 128610 tetrahedra in queue.
2476 insertions, added 560 points, 116391 tetrahedra in queue.
3300 insertions, added 523 points, 73871 tetrahedra in queue.
4399 insertions, added 397 points, 746 tetrahedra in queue.
Refinement seconds: 3.35652
Smoothing vertices...
Mesh smoothing seconds: 2.36935
Improving mesh...
Mesh improvement seconds: 0.199379
Jettisoning redundant points.
Writing nodes.
Writing elements.
Writing faces.
Writing edges.
Output seconds: 0.01441
Total running seconds: 6.39403
Statistics:
Input points: 3137
Input facets: 6262
Input segments: 9393
Input holes: 2
Input regions: 0
Mesh points: 8158
Mesh tetrahedra: 40383
Mesh faces: 83898
Mesh faces on exterior boundary: 6264
Mesh faces on input facets: 6264
Mesh edges on input segments: 9394
Steiner points on input segments: 1
Steiner points inside domain: 5020
Done meshing using TetGen!
Volume mesher did not preserve surface elements - data transfer will NOT be possible.
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - Wing1
Boundary condition name - Wing2
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 0.5901.
Angle of attack (AoA): 1 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 50 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 15.8114 m.
Surface(s) where the force coefficients are evaluated and
their reference origin for moment computation:
- BC_1 (0, 0, 0).
- BC_2 (0, 0, 0) m.
Surface(s) plotted in the output file: BC_1, BC_2.
Input mesh file name: ../myMesh/tetgen_0.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| PARAVIEW| 250|
| SURFACE_PARAVIEW| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_pyCAPS_SU2_Tetgen.dat.
Surface file name: surface_flow_pyCAPS_SU2_Tetgen.
Volume file name: flow_pyCAPS_SU2_Tetgen.
Restart file name: restart_flow_pyCAPS_SU2_Tetgen.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
| | BC_2|
+-----------------------------------------------------------------------+
| Far-field| BC_3|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
8158 grid points.
40383 volume elements.
3 surface markers.
4468 boundary elements in index 0 (Marker = BC_1).
1270 boundary elements in index 1 (Marker = BC_2).
526 boundary elements in index 2 (Marker = BC_3).
40383 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 2.08926e+06.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 414.134. Mean K: 30.5804. Standard deviation K: 37.5377.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 1.92303| 83.9055|
| CV Face Area Aspect Ratio| 1.55295| 3521.13|
| CV Sub-Volume Ratio| 1.01617| 206050|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 8158| 1/1.00| 10|
| 1| 1352| 1/6.03| 8.23927|
| 2| 218| 1/6.2| 6.72677|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 7.90569 m.
Wetted area = 120.046 m^2.
Area projection in the x-plane = 10.7914 m^2, y-plane = 4.58502 m^2, z-plane = 57.287 m^2.
Max. coordinate in the x-direction = 12.6407 m, y-direction = 7.90569 m, z-direction = 0.557773 m.
Min. coordinate in the x-direction = -0.00409054 m, y-direction = -7.90569 m, z-direction = -0.41192 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Boundary marker BC_2 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 226952| 1| m^2/s^2| 226952|
| Velocity-X| 200.779| 1| m/s| 200.779|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 3.50461| 1| m/s| 3.50461|
| Velocity Magnitude| 200.809| 1| m/s| 200.809|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 0.5901|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 1.9393e-01| 0.616193| 3.048153| 2.091399| 6.107088| 1.805051|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 2.0665e-01| 0.775229| 3.247319| 3.001437| 6.275319| 2.174893|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 2.0592e-01| 0.702974| 3.288113| 3.247932| 6.198943| 3.210083|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 2.0628e-01| 0.601014| 3.220958| 3.293492| 6.064222| 4.596839|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 2.0933e-01| 0.593648| 3.197132| 3.233731| 6.058200| 5.787584|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 0.593648| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_pyCAPS_SU2_Tetgen.dat |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
|CSV file |surface_flow_pyCAPS_SU2_Tetgen.csv |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
|Paraview |flow_pyCAPS_SU2_Tetgen.vtu |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
|Paraview surface |surface_flow_pyCAPS_SU2_Tetgen.vtu |
Writing the forces breakdown file (forces_breakdown_pyCAPS_SU2_Tetgen.dat).
+-----------------------------------------------------------------------+
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = 0.759974 Cd = 0.131311
Cmx = -0.003194 Cmy = -0.212257 Cmz = 0.000553
Cx = 0.118028 Cy = 0.000335 Cz = 0.76215
real 0m19.451s
user 0m16.870s
sys 0m0.416s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_and_Tetgen_PyTest.py passed (as expected)
=================================================
=================================================
+ echo 'su2_X43a_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
su2_X43a_PyTest.py test;
+ python -u su2_X43a_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = x43A, index = 1
Name = Farfield, index = 2
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 0
Getting surface mesh for body 1 (of 2)
Getting surface mesh for body 2 (of 2)
Body 1 (of 2)
Number of nodes = 3817
Number of elements = 7634
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 7634
Number of quadrilateral elements = 0
Body 2 (of 2)
Number of nodes = 5654
Number of elements = 11304
Number of node elements = 0
Number of line elements = 0
Number of triangle elements = 11304
Number of quadrilateral elements = 0
----------------------------
Total number of nodes = 9471
Total number of elements = 18938
Writing TECPLOT file: egadsTessMesh_Surf_0.dat ....
Finished writing TECPLOT file
Writing TECPLOT file: egadsTessMesh_Surf_1.dat ....
Finished writing TECPLOT file
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 2
Name = x43A, index = 1
Name = Farfield, index = 2
Number of surface: nodes - 9471, elements - 18938
Getting volume mesh
Generating volume mesh using TetGen.....
Tetgen input string = pYq1.500/0.000T1.00e-16A
Delaunizing vertices...
Delaunay seconds: 0.322616
Creating surface mesh ...
Surface mesh seconds: 0.093419
Recovering boundaries...
Warning: 4 segments are not recovered.
Boundary recovery seconds: 0.760079
Removing exterior tetrahedra ...
Spreading region attributes.
Exterior tets removal seconds: 0.055066
Suppressing Steiner points ...
Steiner suppression seconds: 7e-06
Recovering Delaunayness...
Delaunay recovery seconds: 0.084075
Refining mesh...
12628 insertions, added 5171 points, 10497 tetrahedra in queue.
Refinement seconds: 3.63655
Smoothing vertices...
Mesh smoothing seconds: 2.80464
Improving mesh...
Mesh improvement seconds: 0.270865
Jettisoning redundant points.
Writing nodes.
Writing elements.
Writing faces.
Writing edges.
Output seconds: 0.024568
Total running seconds: 8.0796
Statistics:
Input points: 9471
Input facets: 18938
Input segments: 28407
Input holes: 1
Input regions: 0
Mesh points: 14824
Mesh tetrahedra: 61034
Mesh faces: 131539
Mesh faces on exterior boundary: 18942
Mesh faces on input facets: 18942
Mesh edges on input segments: 28409
Steiner points on input segments: 2
Steiner points inside domain: 5351
Done meshing using TetGen!
Volume mesher did not preserve surface elements - data transfer will NOT be possible.
Writing SU2 file ....
Finished writing SU2 file
Getting CFD boundary conditions
Boundary condition name - Farfield
Boundary condition name - x43A
Done getting CFD boundary conditions
Warning: The su2 cfg file will be overwritten!
Write SU2 configuration file for version "BlackBird (7.4.0) "
Running SU2......
-------------------------------------------------------------------------
| ___ _ _ ___ |
| / __| | | |_ ) Release 7.4.0 "Blackbird" |
| \__ \ |_| |/ / |
| |___/\___//___| Suite (Computational Fluid Dynamics Code) |
| |
-------------------------------------------------------------------------
| SU2 Project Website: https://su2code.github.io |
| |
| The SU2 Project is maintained by the SU2 Foundation |
| (http://su2foundation.org) |
-------------------------------------------------------------------------
| Copyright 2012-2022, SU2 Contributors |
| |
| SU2 is free software; you can redistribute it and/or |
| modify it under the terms of the GNU Lesser General Public |
| License as published by the Free Software Foundation; either |
| version 2.1 of the License, or (at your option) any later version. |
| |
| SU2 is distributed in the hope that it will be useful, |
| but WITHOUT ANY WARRANTY; without even the implied warranty of |
| MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
| Lesser General Public License for more details. |
| |
| You should have received a copy of the GNU Lesser General Public |
| License along with SU2. If not, see <http://www.gnu.org/licenses/>. |
-------------------------------------------------------------------------
Parsing config file for zone 0
----------------- Physical Case Definition ( Zone 0 ) -------------------
Compressible Euler equations.
Mach number: 3.5.
Angle of attack (AoA): 3 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference area is 1 m^2.
The semi-span will be computed using the max y(3D) value.
The reference length is 1 m.
Reference origin for moment evaluation is (0, 0, 0).
Surface(s) where the force coefficients are evaluated: BC_1.
Surface(s) plotted in the output file: BC_1.
Input mesh file name: ../myMesh/tetgen_0.su2
--------------- Space Numerical Integration ( Zone 0 ) ------------------
Roe (with entropy fix = 0.001) solver for the flow inviscid terms.
Standard Roe without low-dissipation function.
Second order integration in space, with slope limiter.
Venkatakrishnan slope-limiting method, with constant: 0.05.
The reference element size is: 1.
Gradient for upwind reconstruction: inverse-distance weighted Least-Squares.
Gradient for viscous and source terms: inverse-distance weighted Least-Squares.
--------------- Time Numerical Integration ( Zone 0 ) ------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
FGMRES is used for solving the linear system.
Using a ILU(0) preconditioning.
Convergence criteria of the linear solver: 1e-06.
Max number of linear iterations: 10.
V Multigrid Cycle, with 2 multigrid levels.
Damping factor for the residual restriction: 0.75.
Damping factor for the correction prolongation: 0.75.
No CFL adaptation.
+-------------------------------------------+
| MG Level| Presmooth|PostSmooth|CorrectSmo|
+-------------------------------------------+
| 0| 1| 0| 0|
| 1| 2| 0| 0|
| 2| 3| 0| 0|
+-------------------------------------------+
Courant-Friedrichs-Lewy number: 10
------------------ Convergence Criteria ( Zone 0 ) ---------------------
Maximum number of solver subiterations: 5.
Begin convergence monitoring at iteration 5.
Residual minimum value: 1e-14.
Cauchy series min. value: 1e-10.
Number of Cauchy elements: 100.
Begin windowed time average at iteration 0.
-------------------- Output Information ( Zone 0 ) ----------------------
File writing frequency:
+------------------------------------+
| File| Frequency|
+------------------------------------+
| RESTART| 250|
| SURFACE_CSV| 250|
| PARAVIEW| 250|
| SURFACE_PARAVIEW| 250|
+------------------------------------+
Writing the convergence history file every 1 inner iterations.
Writing the screen convergence history every 1 inner iterations.
The tabular file format is CSV (.csv).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown_x43a_Test.dat.
Surface file name: surface_flow_x43a_Test.
Volume file name: flow_x43a_Test.
Restart file name: restart_flow_x43a_Test.dat.
------------- Config File Boundary Information ( Zone 0 ) ---------------
+-----------------------------------------------------------------------+
| Marker Type| Marker Name|
+-----------------------------------------------------------------------+
| Euler wall| BC_1|
+-----------------------------------------------------------------------+
| Far-field| BC_2|
+-----------------------------------------------------------------------+
-------------------- Output Preprocessing ( Zone 0 ) --------------------
WARNING: SURFACE_PRESSURE_DROP can only be computed for at least 2 surfaces (outlet, inlet, ...)
Screen output fields: TIME_ITER, OUTER_ITER, INNER_ITER, CUR_TIME, TIME_STEP, WALL_TIME, RMS_DENSITY, RMS_MOMENTUM-X, RMS_MOMENTUM-Y, RMS_ENERGY, EFFICIENCY
History output group(s): ITER, TIME_DOMAIN, WALL_TIME, RMS_RES, AERO_COEFF
Convergence field(s): RMS_DENSITY
Warning: No (valid) fields chosen for time convergence monitoring. Time convergence monitoring inactive.
Volume output fields: COORDINATES, SOLUTION, PRIMITIVE
------------------- Geometry Preprocessing ( Zone 0 ) -------------------
Three dimensional problem.
14824 grid points.
61034 volume elements.
2 surface markers.
7638 boundary elements in index 0 (Marker = BC_1).
11304 boundary elements in index 1 (Marker = BC_2).
61034 tetrahedra.
Setting point connectivity.
Renumbering points (Reverse Cuthill McKee Ordering).
Recomputing point connectivity.
Setting element connectivity.
Checking the numerical grid orientation.
All volume elements are correctly orientend.
All surface elements are correctly orientend.
Identifying edges and vertices.
Setting the control volume structure.
Volume of the computational grid: 2.67744e+08.
Searching for the closest normal neighbors to the surfaces.
Storing a mapping from global to local point index.
Compute the surface curvature.
Max K: 95.6599. Mean K: 0.525659. Standard deviation K: 2.58024.
Checking for periodicity.
Computing mesh quality statistics for the dual control volumes.
+--------------------------------------------------------------+
| Mesh Quality Metric| Minimum| Maximum|
+--------------------------------------------------------------+
| Orthogonality Angle (deg.)| 0.041314| 83.9178|
| CV Face Area Aspect Ratio| 1.62826| 13202.4|
| CV Sub-Volume Ratio| 1| 1.24042e+07|
+--------------------------------------------------------------+
Setting the multigrid structure.
+-------------------------------------------+
| MG Level| CVs|Aggl. Rate| CFL|
+-------------------------------------------+
| 0| 14824| 1/1.00| 10|
| 1| 2668| 1/5.56| 8.46899|
| 2| 492| 1/5.42| 7.23073|
+-------------------------------------------+
Finding max control volume width.
Semi-span length = 30 m.
Wetted area = 13597 m^2.
Area projection in the x-plane = 761.658 m^2, y-plane = 2062.86 m^2, z-plane = 5463.61 m^2.
Max. coordinate in the x-direction = 150 m, y-direction = 30 m, z-direction = 19 m.
Min. coordinate in the x-direction = 0 m, y-direction = -30 m, z-direction = -10.3 m.
Checking if Euler & Symmetry markers are straight/plane:
Boundary marker BC_1 is NOT a single plane.
Computing wall distances.
-------------------- Solver Preprocessing ( Zone 0 ) --------------------
Inviscid flow: Computing density based on free-stream
temperature and pressure using the ideal gas law.
Force coefficients computed using free-stream values.
-- Models:
+------------------------------------------------------------------------------+
| Viscosity Model| Conductivity Model| Fluid Model|
+------------------------------------------------------------------------------+
| -| -| STANDARD_AIR|
+------------------------------------------------------------------------------+
-- Fluid properties:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Gas Constant| 287.058| 1| N.m/kg.K| 287.058|
| Spec. Heat Ratio| -| -| -| 1.4|
+------------------------------------------------------------------------------+
-- Initial and free-stream conditions:
+------------------------------------------------------------------------------+
| Name| Dim. value| Ref. value| Unit|Non-dim. value|
+------------------------------------------------------------------------------+
| Static Pressure| 101325| 1| Pa| 101325|
| Density| 1.22498| 1| kg/m^3| 1.22498|
| Temperature| 288.15| 1| K| 288.15|
| Total Energy| 916077| 1| m^2/s^2| 916077|
| Velocity-X| 1189.41| 1| m/s| 1189.41|
| Velocity-Y| 0| 1| m/s| 0|
| Velocity-Z| 62.3342| 1| m/s| 62.3342|
| Velocity Magnitude| 1191.04| 1| m/s| 1191.04|
+------------------------------------------------------------------------------+
| Mach Number| -| -| -| 3.5|
+------------------------------------------------------------------------------+
Initialize Jacobian structure (Euler). MG level: 0.
Initialize Jacobian structure (Euler). MG level: 1.
Initialize Jacobian structure (Euler). MG level: 2.
------------------- Numerics Preprocessing ( Zone 0 ) -------------------
----------------- Integration Preprocessing ( Zone 0 ) ------------------
------------------- Iteration Preprocessing ( Zone 0 ) ------------------
Euler/Navier-Stokes/RANS fluid iteration.
------------------------------ Begin Solver -----------------------------
Simulation Run using the Single-zone Driver
+----------------------------------------------------------------------------------------------------------------------------------------------+
| Time_Iter| Outer_Iter| Inner_Iter| Cur_Time| Time_Step| Time(sec)| rms[Rho]| rms[RhoU]| rms[RhoV]| rms[RhoE]| CEff|
+----------------------------------------------------------------------------------------------------------------------------------------------+
| 0| 0| 0| 0.0000e+00| 0.0000e+00| 3.5015e-01| 2.731645| 5.665596| 4.729423| 8.731121| -0.374100|
| 0| 0| 1| 0.0000e+00| 0.0000e+00| 3.6996e-01| 3.120118| 6.139645| 5.659982| 9.120238| -0.138499|
| 0| 0| 2| 0.0000e+00| 0.0000e+00| 3.5774e-01| 3.198604| 6.246170| 5.767210| 9.165358| -0.054805|
| 0| 0| 3| 0.0000e+00| 0.0000e+00| 3.5175e-01| 3.243196| 6.288748| 5.704421| 9.196215| -0.048476|
| 0| 0| 4| 0.0000e+00| 0.0000e+00| 3.4977e-01| 3.234245| 6.291775| 5.521178| 9.205466| -0.072036|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 5) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[Rho]| 3.23424| < -14| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow_x43a_Test.dat |
Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
|CSV file |surface_flow_x43a_Test.csv |
Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
|Paraview |flow_x43a_Test.vtu |
Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
|Paraview surface |surface_flow_x43a_Test.vtu |
Writing the forces breakdown file (forces_breakdown_x43a_Test.dat).
+-----------------------------------------------------------------------+
Warning: there are 131 non-physical points in the solution.
Warning: 63 reconstructed states for upwinding are non-physical.
------------------------- Solver Postprocessing -------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
Total Force - Pressure + Viscous
Cl = -8.581041 Cd = 119.121674
Cmx = -19.065106 Cmy = 9458.970655 Cmz = 200.291547
Cx = 119.407518 Cy = 2.431409 Cz = -2.334934
real 0m46.308s
user 0m50.266s
sys 0m0.694s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case su2_X43a_PyTest.py passed (as expected)
=================================================
./execute_PyTestRegression.sh: line 403: ulimit: stack size: cannot modify limit: Operation not permitted
flowCart: /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//flowCart
=================================================
+ echo 'cart3d_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
cart3d_PyTest.py test;
+ python -u cart3d_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Loading AIM
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Body size = 3.796888
Tessellating body 1 with MaxEdge = 0.094922 Sag = 0.003797 Angle = 15.000000
Executing: autoInputs -r 30.000000 -nDiv 6 -maxR 9 > autoInputs.out
Executing: ./aero.csh > aero.out
Sat Mar 11 00:39:15 EST 2023
-rwx------ 1 jenkins 77175 Mar 11 00:39 ./aero.csh
CART3D env variable set to: /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28
CART3D_ARCH env variable set to: OSX64_ICC
Using codes:
-rwxr-xr-- 1 jenkins 1558776 Oct 27 2020 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//cubes
-rwxr-xr-- 1 jenkins 1292272 Oct 27 2020 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//mgPrep
-rwxr-xr-- 1 jenkins 4000008 Oct 27 2020 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//flowCart
-rwxr-xr-- 1 jenkins 4374960 Oct 27 2020 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//xsensit
-rwxr-xr-- 1 jenkins 4168768 Oct 27 2020 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//adjointCart
-rwxr-xr-- 1 jenkins 12944448 Oct 27 2020 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//adjointErrorEst_quad
-rwxr-xr-- 1 jenkins 2952992 Oct 27 2020 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//adapt
md5 checksums:
83388126060516d9809ae90219324ec2 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//cubes
b931a45f0a6528e9e0a09dd8bbdc3112 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//mgPrep
e6b7a582f48fdfcfa826ace8e16ae775 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//flowCart
0a21c9bbb7cbe180fb260828930d5e51 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//xsensit
4700b7139293eedfe3cf9ec973695073 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//adjointCart
7daf88cd4774ca932186a9814f2f180d /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//adjointErrorEst_quad
34e91e2cc2f93cdcf420065832acd385 /Users/jenkins/util/cart3d/cart3d_v1.5.7_OSX64_ICC--20.10.28/bin/OSX64_ICC//adapt
Building initial mesh
ERROR: CUBES failed in /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/cart3dTest/Scratch/cart3dAIM0/inputs/adapt00
===> ERROR: Cannot execute cubes -- please contact Cart3D developers.
Traceback (most recent call last):
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/cart3d_PyTest.py", line 61, in <module>
print ("C_A " + str(myAnalysis.output.C_A))
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/problem.py", line 1950, in __getattr__
return self._capsItems[name].value
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/problem.py", line 1880, in value
return self._valObj.getValue()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed
return func(*args, **kwargs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 1968, in getValue
if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs))
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus
raise CAPSError(status, msg=msg, errors=errors)
pyCAPS.caps.CAPSError: CAPS_EXECERR:
================================================================================
================================================================================
real 0m9.826s
user 0m6.616s
sys 0m0.320s
+ status=1
+ set +x
=================================================
CAPS verification (using pyCAPS) case cart3d_PyTest.py failed (as NOT expected)
=================================================
=================================================
+ echo 'cart3d_OpenMDAO_3_alpha_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
cart3d_OpenMDAO_3_alpha_PyTest.py test;
+ python -u cart3d_OpenMDAO_3_alpha_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
----------------------------------------
>>> alpha [2.]
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 1
Name = Wing, index = 1
Getting CFD design variables.......
Number of design variables - 1
Design Variable name - alpha
Done getting CFD design variables
Getting CFD functional.......
Number of design variables - 1
Objective name - CL2
Done getting CFD functional
Body size = 3.625615
Tessellating body 1 with MaxEdge = 0.090640 Sag = 0.003626 Angle = 15.000000
Executing: autoInputs -r 30.000000 -nDiv 5 -maxR 7 -mesh2d > autoInputs.out
o Evaluating Cart3D functionals and/or gradients
ATTENTION: using static geometry ../inputs/Components.i.tri
(00:39:27) Running aero.csh on 2 core(s) in M0.5901A2B0_DP1
c3d_runAero.pl FAILED: aero.csh failed
Read OUT file in /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/Cart3D_OpenMDAO_v3_alpha/Scratch/cart3d/design/M0.5901A2B0_DP1
ERROR c3d_objGrad.csh: c3d_runAero.pl failed
Traceback (most recent call last):
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/system.py", line 2958, in _call_user_function
yield
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/explicitcomponent.py", line 294, in _compute_wrapper
self.compute(self._inputs, self._outputs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/cart3d_OpenMDAO_3_alpha_PyTest.py", line 72, in compute
outputs['CL2'] = cart3d.dynout["CL2"].value
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/problem.py", line 1991, in value
valObj = self._analysisObj.childByName(caps.oType.VALUE, caps.sType.ANALYSISDYNO, self._name)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed
return func(*args, **kwargs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 1331, in childByName
if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs))
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus
raise CAPSError(status, msg=msg, errors=errors)
pyCAPS.caps.CAPSError: CAPS_EXECERR:
================================================================================
================================================================================
During handling of the above exception, another exception occurred:
Traceback (most recent call last):
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/cart3d_OpenMDAO_3_alpha_PyTest.py", line 237, in <module>
omProblem.run_driver()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/utils/hooks.py", line 131, in execute_hooks
ret = f(*args, **kwargs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/problem.py", line 686, in run_driver
return self.driver.run()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/drivers/scipy_optimizer.py", line 276, in run
model.run_solve_nonlinear()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/system.py", line 4678, in run_solve_nonlinear
self._solve_nonlinear()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/group.py", line 2534, in _solve_nonlinear
self._nonlinear_solver._solve_with_cache_check()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/solvers/nonlinear/nonlinear_runonce.py", line 26, in _solve_with_cache_check
self.solve() # don't use caching
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/solvers/nonlinear/nonlinear_runonce.py", line 45, in solve
self._gs_iter()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/solvers/solver.py", line 793, in _gs_iter
subsys._solve_nonlinear()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/explicitcomponent.py", line 320, in _solve_nonlinear
self._compute_wrapper()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/explicitcomponent.py", line 294, in _compute_wrapper
self.compute(self._inputs, self._outputs)
File "/Users/jenkins/util/ESP/Python/ESP_Python-3.9.13/lib/python3.9/contextlib.py", line 137, in __exit__
self.gen.throw(typ, value, traceback)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/system.py", line 2964, in _call_user_function
raise err_type(
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/system.py", line 2958, in _call_user_function
yield
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/explicitcomponent.py", line 294, in _compute_wrapper
self.compute(self._inputs, self._outputs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/cart3d_OpenMDAO_3_alpha_PyTest.py", line 72, in compute
outputs['CL2'] = cart3d.dynout["CL2"].value
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/problem.py", line 1991, in value
valObj = self._analysisObj.childByName(caps.oType.VALUE, caps.sType.ANALYSISDYNO, self._name)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed
return func(*args, **kwargs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 1331, in childByName
if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs))
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus
raise CAPSError(status, msg=msg, errors=errors)
pyCAPS.caps.CAPSError: CAPS error code 'cart3dSystem' <class Cart3dAnalysis>: Error calling compute(), CAPS_EXECERR:
================================================================================
================================================================================
(undefined error)
real 0m12.356s
user 0m6.916s
sys 0m0.528s
+ status=1
+ set +x
=================================================
CAPS verification (using pyCAPS) case cart3d_OpenMDAO_3_alpha_PyTest.py failed (as NOT expected)
=================================================
=================================================
+ echo 'cart3d_OpenMDAO_3_twist_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
cart3d_OpenMDAO_3_twist_PyTest.py test;
+ python -u cart3d_OpenMDAO_3_twist_PyTest.py -outLevel=0
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
----------------------------------------
>>> 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
(00:39:45) Running aero.csh on 2 core(s) in M0.5901A0B0_DP1
c3d_runAero.pl FAILED: aero.csh failed
Read OUT file in /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/Cart3D_OpenMDAO_v3_twist/Scratch/cart3d/design/M0.5901A0B0_DP1
ERROR c3d_objGrad.csh: c3d_runAero.pl failed
Traceback (most recent call last):
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/system.py", line 2958, in _call_user_function
yield
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/explicitcomponent.py", line 294, in _compute_wrapper
self.compute(self._inputs, self._outputs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/cart3d_OpenMDAO_3_twist_PyTest.py", line 73, in compute
outputs['CL2'] = cart3d.dynout["CL2"].value
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/problem.py", line 1991, in value
valObj = self._analysisObj.childByName(caps.oType.VALUE, caps.sType.ANALYSISDYNO, self._name)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed
return func(*args, **kwargs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 1331, in childByName
if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs))
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus
raise CAPSError(status, msg=msg, errors=errors)
pyCAPS.caps.CAPSError: CAPS_EXECERR:
================================================================================
================================================================================
During handling of the above exception, another exception occurred:
Traceback (most recent call last):
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/cart3d_OpenMDAO_3_twist_PyTest.py", line 257, in <module>
omProblem.run_driver()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/utils/hooks.py", line 131, in execute_hooks
ret = f(*args, **kwargs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/problem.py", line 686, in run_driver
return self.driver.run()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/drivers/scipy_optimizer.py", line 276, in run
model.run_solve_nonlinear()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/system.py", line 4678, in run_solve_nonlinear
self._solve_nonlinear()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/group.py", line 2534, in _solve_nonlinear
self._nonlinear_solver._solve_with_cache_check()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/solvers/nonlinear/nonlinear_runonce.py", line 26, in _solve_with_cache_check
self.solve() # don't use caching
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/solvers/nonlinear/nonlinear_runonce.py", line 45, in solve
self._gs_iter()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/solvers/solver.py", line 793, in _gs_iter
subsys._solve_nonlinear()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/explicitcomponent.py", line 320, in _solve_nonlinear
self._compute_wrapper()
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/explicitcomponent.py", line 294, in _compute_wrapper
self.compute(self._inputs, self._outputs)
File "/Users/jenkins/util/ESP/Python/ESP_Python-3.9.13/lib/python3.9/contextlib.py", line 137, in __exit__
self.gen.throw(typ, value, traceback)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/system.py", line 2964, in _call_user_function
raise err_type(
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/system.py", line 2958, in _call_user_function
yield
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/venv/lib/python3.9/site-packages/openmdao/core/explicitcomponent.py", line 294, in _compute_wrapper
self.compute(self._inputs, self._outputs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/pyCAPS/cart3d_OpenMDAO_3_twist_PyTest.py", line 73, in compute
outputs['CL2'] = cart3d.dynout["CL2"].value
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/problem.py", line 1991, in value
valObj = self._analysisObj.childByName(caps.oType.VALUE, caps.sType.ANALYSISDYNO, self._name)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 999, in wrapper_checkClosed
return func(*args, **kwargs)
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 1331, in childByName
if stat: _raiseStatus(stat, errors=capsErrs(nErr, errs))
File "/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/CAPS/pyCAPS/pyCAPS/caps.py", line 822, in _raiseStatus
raise CAPSError(status, msg=msg, errors=errors)
pyCAPS.caps.CAPSError: CAPS error code 'cart3dSystem' <class Cart3dAnalysis>: Error calling compute(), CAPS_EXECERR:
================================================================================
================================================================================
(undefined error)
real 0m17.968s
user 0m15.214s
sys 0m0.517s
+ status=1
+ set +x
=================================================
CAPS verification (using pyCAPS) case cart3d_OpenMDAO_3_twist_PyTest.py failed (as NOT expected)
=================================================
=================================================
+ echo 'fun3d_Morph_PyTest.py test;'
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
fun3d_Morph_PyTest.py test;
+ python -u fun3d_Morph_PyTest.py -outLevel=0 -noAnalysis
+ tee -a /Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1/ESP/DARWINM1/examples/regressionTest/pyCAPSlog.txt
Mapping capsGroup attributes ................
Number of unique capsGroup attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
Mapping capsMesh attributes ................
Number of unique capsMesh attributes = 3
Name = Wing1, index = 1
Name = Wing2, index = 2
Name = Farfield, index = 3
AFLR4 : Proximity BG Surface Grid Generation Skipped
AFLR4 : No Modifications Required
Writing TECPLOT file: pyCAPS_AFLR4_AFLR3.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 9.14.6
AFLR2 : Version Date 11/20/22 @ 09:21PM
AFLR2 : Compile OS Darwin 22.3.0 arm64
AFLR2 : Compile Date 02/27/23 @ 03:36PM
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 11.3.17
AFLR4 : Version Date 03/03/23 @ 03:12PM
AFLR4 : Compile OS Darwin 22.3.0 arm64
AFLR4 : Compile Date 03/03/23 @ 03:13PM
AFLR4 : Copyright 1994-2021, D.L. Marcum
AFLR4 : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.23
EGADS : OpenCASCADE Version 7.4.1
EGADS : ---------------------------------------
EGADS : ---------------------------------------
EGADS : Engineering Geometry Aircraft Design System
EGADS : Version 1.23
EGADS : OpenCASCADE Version 7.4.1
EGADS : ---------------------------------------
Volume mesh:
Number of nodes = 82911
Number of elements = 483743
Number of triangles = 15694
Number of quadrilatarals = 0
Number of tetrahedrals = 468049
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 0m31.569s
user 0m22.027s
sys 0m0.512s
+ status=0
+ set +x
=================================================
CAPS verification (using pyCAPS) case fun3d_Morph_PyTest.py passed (as expected)
=================================================
*************************************************
*************************************************
=================================================
Did not run examples for:
Fun3D
=================================================
=================================================
Summary of examples NOT finished as expected
cart3d_PyTest.py
cart3d_OpenMDAO_3_alpha_PyTest.py
cart3d_OpenMDAO_3_twist_PyTest.py
See pyCAPSlog.txt for more details.
=================================================
=================================================
=================================================
++ true
[GNU C Compiler (gcc)] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1')
[GNU C Compiler (gcc)] Successfully parsed console log
[GNU C Compiler (gcc)] -> found 0 issues (skipped 0 duplicates)
[GNU C Compiler (gcc)] Skipping post processing
[GNU C Compiler (gcc)] No filter has been set, publishing all 0 issues
[GNU C Compiler (gcc)] Repository miner is not configured, skipping repository mining
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1')
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Successfully parsed console log
[Clang] -> found 0 issues (skipped 0 duplicates)
[Clang] Parsing console log (workspace: '/Users/jenkins/workspace/ESP_UndefinedCaps/7.4/CAPS/CFD/DARWINM1')
[Clang] Skipping post processing
[Clang] No filter has been set, publishing all 0 issues
[Clang] Repository miner is not configured, skipping repository mining
[Static Analysis] Reference build recorder is not configured
[Static Analysis] Obtaining reference build from same job (7.4,CAPS/CFD,DARWINM1,viggen)
[Static Analysis] Using reference build 'ESP_UndefinedCaps/CASREV=7.4,ESPTEST=CAPS/CFD,ESP_ARCH=DARWINM1,buildnode=viggen #176' to compute new, fixed, and outstanding issues
[Static Analysis] Issues delta (vs. reference build): outstanding: 0, new: 0, fixed: 0
[Static Analysis] Evaluating quality gates
[Static Analysis] -> PASSED - Total (any severity): 0 - Quality Gate: 1
[Static Analysis] -> All quality gates have been passed
[Static Analysis] Health report is disabled - skipping
[Static Analysis] Created analysis result for 0 issues (found 0 new issues, fixed 0 issues)
[Static Analysis] Attaching ResultAction with ID 'analysis' to build 'ESP_UndefinedCaps/CASREV=7.4,ESPTEST=CAPS/CFD,ESP_ARCH=DARWINM1,buildnode=viggen #177'.
[Checks API] No suitable checks publisher found.
Build step 'Console output (build log) parsing' changed build result to FAILURE
[PostBuildScript] - [INFO] Executing post build scripts.
[PostBuildScript] - [INFO] build step #0 should only be executed on MATRIX
[WS-CLEANUP] Deleting project workspace...
[WS-CLEANUP] Skipped based on build state FAILURE
Finished: FAILURE
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