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Problem with rhoSimplecFoam - nan

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Old   January 8, 2012, 11:51
Default Problem with rhoSimplecFoam - nan
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Daniel
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Hello all,

I am trying to evolve my incompressible, steady-state 2D airfoil simulation into a compressible, steady-state simulation. I have selected rhoSimplecFoam as a solver, however I cannot get the simulation to run past 9 iterations without getting "nan" for the residuals first with k and omega, then the next iteration has residuals of "nan" for all variables. I have tried playing with the boundary conditions and solver parameters to no avail. Would someone please suggest where I could start looking? Some information:

1. The simulation runs successfully and with results that compare well to experimental data in simpleFoam;
2. The mesh is a c-grid with ~42000 cells and a boundary 10c from the NACA 0012 airfoil;
3. Angle of attack is 13 degrees, implemented by introducing a inlet velocity at that angle (mesh pic attached);
4. Boundary conditions are as attached;
5. k-omega turbulence model;
6. fvSolution & fvSchemes copied from tutorial rhoSimplecFoam\squareBend.

Thank you for any suggestions,

Dan
Attached Images
File Type: jpg Meshpic.jpg (53.0 KB, 12 views)
Attached Files
File Type: zip m3_a13_r6.zip (6.5 KB, 11 views)
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