[McAero]

Hello All,
I hope someone can help me,
I am Student and still learning CFD , i wanna make computations for NACA0012 2D i tried many configurations but it`s not converging , always diverging
the physical case is :
Navier stokes equations Incompressible
AoA : zero
Re No. : 649328
Velocity : 45 m/sec in The X direction only
my mesh is a c shape with inlet named 'OPEN' as the c
and the sym is 'FLUID'
and the outlet is 'OUT'
and the foil named 'WALL'
I hope i cant` find some , i`d really appreciate it ))
Kindly find attached the cfg file and cgns

Thanks a lot

[McAero]

Here is the configuration file , i couldn`t upload the cgns

[akoodlyr]

Have you tried using the config file settings from https://github.com/su2code/SU2/tree/..._rans/naca0012 ?

[McAero]

Thanks very much for your reply
Yes i tried but still diverging

[akoodlyr]

Have you used the mesh files from

https://github.com/su2code/TestCases..._rans/naca0012 ?

Also, can you get rid of the outlet and inlet boundary conditions and instead set OPEN and OUT as FARFIELD?

[McAero]

Thanks very much for your support
i have replaced the Far-field with ( OPEN, OUT ) but it`s still diverging very fast
Thanks again for your support

[akoodlyr]

Ok, can you try to use the mesh and BCs from this https://turbmodels.larc.nasa.gov/naca0012_val.html ?

It is a validation case on NACA 0012 but the trailing edge is modified to be sharp. They have a bunch of (unstructured) CGNS mesh files there (https://turbmodels.larc.nasa.gov/naca0012_grids.html). You can download them. Use the cfg file from the link I gave previously and change the mesh name and markers. Can you run the case and see if it still diverges?

[McAero]

Thanks a lot and sorry for the late reply
But unfortunately it`s all 3D cgns files
i and i don`t know th names for the markers