[jvbustelo]

Hello everyone,

I am trying open-source meshers like GMSH and Salome v7.8.0 and I am using the Onera M6 inviscid case to validate my meshes since the SU2's Test Cases have a very good mesh made with Pointwise. The goal is to achieve similar results to this mesh with open-source meshers.

Salome is the one that I found more powerful and I got the cfdmsh plugin to be able to export the mesh in SU2 format directly with the markers included.

However, when running this mesh I am obtaining the following error:

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|    ___ _   _ ___                                                      |
|   / __| | | |_  )   Release 4.2.0  "Cardinal"                         |
|   \__ \ |_| |/ /                                                      |
|   |___/\___//___|   Suite (Computational Fluid Dynamics Code)         |
|                                                                       |
-------------------------------------------------------------------------
| SU2 Lead Dev.: Dr. Francisco Palacios, Francisco.D.Palacios@boeing.com|
|                Dr. Thomas D. Economon, economon@stanford.edu          |
-------------------------------------------------------------------------
| SU2 Developers:                                                       |
| - Prof. Juan J. Alonso's group at Stanford University.                |
| - Prof. Piero Colonna's group at Delft University of Technology.      |
| - Prof. Nicolas R. Gauger's group at Kaiserslautern U. of Technology. |
| - Prof. Alberto Guardone's group at Polytechnic University of Milan.  |
| - Prof. Rafael Palacios' group at Imperial College London.            |
-------------------------------------------------------------------------
| Copyright (C) 2012-2016 SU2, the open-source CFD code.                |
|                                                                       |
| 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/>.   |
-------------------------------------------------------------------------

------------------------ Physical Case Definition -----------------------
Compressible Euler equations.
Mach number: 0.8395.
Angle of attack (AoA): 3.06 deg, and angle of sideslip (AoS): 0 deg.
No restart solution, use the values at infinity (freestream).
Dimensional simulation.
The reference length/area will be computed using y(2D) or z(3D) projection.
The reference length (moment computation) is 1.
Reference origin (moment computation) is (0.25, 0, 0).
Surface(s) where the force coefficients are evaluated: WING.
Surface(s) where the objective function is evaluated: WING.
Surface(s) plotted in the output file: WING.
Surface(s) belonging to the Fluid-Structure Interaction problem: 
Surface(s) affected by the design variables: WING.
Input mesh file name: Mesh_1.su2

---------------------- Space Numerical Integration ----------------------
Jameson-Schmidt-Turkel scheme for the flow inviscid terms.
JST viscous coefficients (1st, 2nd & 4th): 0.15, 0.5, 0.02.
The method includes a grid stretching correction (p = 0.3).
Second order integration.
Gradient Computation using weighted Least-Squares method.

---------------------- Time Numerical Integration -----------------------
Local time stepping (steady state simulation).
Euler implicit method for the flow equations.
W Multigrid Cycle, with 3 multigrid levels.
Damping factor for the residual restriction: 0.9.
Damping factor for the correction prolongation: 0.9.
No CFL adaptation.
Multigrid Level:                       0     1     2     3
Courant-Friedrichs-Lewy number:        5
MG PreSmooth coefficients:             1     2     3     3
MG PostSmooth coefficients:            0     0     0     0
MG CorrecSmooth coefficients:          0     0     0     0

------------------------- Convergence Criteria --------------------------
Maximum number of iterations: 99999.
Reduce the density residual 8 orders of magnitude.
The minimum bound for the density residual is 10^(-12).
Start convergence criteria at iteration 25.

-------------------------- Output Information ---------------------------
Writing a flow solution every 100 iterations.
Writing the convergence history every 1 iterations.
The output file format is Paraview ASCII (.vtk).
Convergence history file name: history.
Forces breakdown file name: forces_breakdown.dat.
Surface flow coefficients file name: surface_flow.
Flow variables file name: flow.
Restart flow file name: restart_flow.dat.

------------------- Config File Boundary Information --------------------
Euler wall boundary marker(s): WING.
Far-field boundary marker(s): FARFIELD.
Symmetry plane boundary marker(s): SYMMETRY.

---------------------- Read Grid File Information -----------------------
Three dimensional problem.
212676 interior elements before parallel partitioning.
Calling the partitioning functions.
Building the graph adjacency structure.
Traceback (most recent call last):
  File "/usr/local/bin/parallel_computation.py", line 110, in <module>
    main()
  File "/usr/local/bin/parallel_computation.py", line 61, in main
    options.compute      )
  File "/usr/local/bin/parallel_computation.py", line 88, in parallel_computation
    info = SU2.run.CFD(config) 
  File "/usr/local/bin/SU2/run/interface.py", line 115, in CFD
    run_command( the_Command )
  File "/usr/local/bin/SU2/run/interface.py", line 295, in run_command
    raise exception , message
RuntimeError: Path = /home/openfoam/TestCases/euler/Try/,
Command = mpirun -n 2 /usr/local/bin/SU2_CFD config_CFD.cfg
SU2 process returned error '134'
terminate called after throwing an instance of 'std::bad_alloc'
  what():  std::bad_alloc
[openFOAM:05093] *** Process received signal ***
[openFOAM:05093] Signal: Aborted (6)
[openFOAM:05093] Signal code:  (-6)
[openFOAM:05093] [ 0] /lib/x86_64-linux-gnu/libpthread.so.0(+0x10330) [0x7f6126498330]
[openFOAM:05093] [ 1] /lib/x86_64-linux-gnu/libc.so.6(gsignal+0x37) [0x7f61260f9c37]
[openFOAM:05093] [ 2] /lib/x86_64-linux-gnu/libc.so.6(abort+0x148) [0x7f61260fd028]
[openFOAM:05093] [ 3] /usr/lib/x86_64-linux-gnu/libstdc++.so.6(_ZN9__gnu_cxx27__verbose_terminate_handlerEv+0x155) [0x7f6126c22535]
[openFOAM:05093] [ 4] /usr/lib/x86_64-linux-gnu/libstdc++.so.6(+0x5e6d6) [0x7f6126c206d6]
[openFOAM:05093] [ 5] /usr/lib/x86_64-linux-gnu/libstdc++.so.6(+0x5e703) [0x7f6126c20703]
[openFOAM:05093] [ 6] /usr/lib/x86_64-linux-gnu/libstdc++.so.6(+0x5e922) [0x7f6126c20922]
[openFOAM:05093] [ 7] /usr/lib/x86_64-linux-gnu/libstdc++.so.6(_Znwm+0x7d) [0x7f6126c20e0d]
[openFOAM:05093] [ 8] /usr/lib/x86_64-linux-gnu/libstdc++.so.6(_Znam+0x9) [0x7f6126c20ea9]
[openFOAM:05093] [ 9] /usr/local/bin/SU2_CFD() [0x8ffbfc]
[openFOAM:05093] [10] /usr/local/bin/SU2_CFD() [0x908e6d]
[openFOAM:05093] [11] /usr/local/bin/SU2_CFD() [0x6041d8]
[openFOAM:05093] [12] /lib/x86_64-linux-gnu/libc.so.6(__libc_start_main+0xf5) [0x7f61260e4f45]
[openFOAM:05093] [13] /usr/local/bin/SU2_CFD() [0x72166b]
[openFOAM:05093] *** End of error message ***
--------------------------------------------------------------------------
mpirun noticed that process rank 0 with PID 5093 on node openFOAM exited on signal 6 (Aborted).
--------------------------------------------------------------------------

I am running in parallel (2 cores). The mesh seems to be fine, comparing to the mesh in test cases it is only lacking the optimization control geometry. Anyways I have tried eliminating from the cfg file the opt part, but the same error appeared.

The mesh file is 10Mb so it is not attachable. I would appreciate any help on the issue.

Thanks in advance!

[maero21]

See my other post, but check whether there is a space in front of e.g. comments in your mesh file. When I had a space in front of everything in my mesh file, that's what ruined everything for me.