[sangeet]

Hello,
I am currently using simpleFoam with SA turbluence model for a 2D simulation of flow over an airfoil, I get physically correct values for the lift coefficients when I operate at low angles of attacks but when i move on to high angles of attack where flow separation occurs, the values become very unphysical. I believe this might be due to the fact that I use zeroGradient as a pressure boundary condition on the airfoil surface.

Am i correct in this? Is there a better pressure boundary condition for separated flow or is there a higher chance of something else going wrong in my simulation?

I copied the settings for fvSchemes and fvSolution from the airfoil2D tutorial case in simpleFoam but used another mesh generated from gmsh. My nut and nuTilda files are also copies of the tutorial case with the neccessary changes like patch names and types.

Thank You

[hokhay]

Hi Sangeet, have you tried other turbulence model like k-OmegaSST? As far as I know SA is only good for high Reynolds number and k-Omega SST would give better result for low Reynolds number. k-Omega is good at capturing boundary layer which is crucial to slender body like airfoil.

[sangeet]

Hi!,
Thank you for replying, i am currently trying out other models including KOmegaSST. I will post my results here when i get my values close enough to the experimental data.

Again, thank you for prompting me to try out other models, i would probably have wasted my time on the BC.