[giammy92]

Hi Foamers,
i'm doing a steady simulation on an airfoil with Re = 1.5e6 using kklomega and solver simpleFoam.
The simulations have given me good results of Cd and Cl until angle of attack 10° using these schemes:
ddtSchemes
{
default steadyState;
}

gradSchemes
{
default Gauss linear;
}

divSchemes
{
default none;
div(phi,U) bounded Gauss linearUpwindV grad(U); ----------> at beginning upwind
div(phi,kt) bounded Gauss upwind;
div(phi,kl) bounded Gauss upwind;
div(phi,omega) bounded Gauss upwind;
div((nuEff*dev(T(grad(U))))) Gauss linear;
}

laplacianSchemes
{
default Gauss linear corrected;
}

interpolationSchemes
{
default linear;
}

snGradSchemes
{
default corrected;
}

fluxRequired
{
default no;
p;
}

but starting from 13° results are worse and starting from 15°, near where the stall is verified, i have more and more oscillations and i know that is normal but it difficult for me individuate the solution and if my schemes are good or they have to change when stall is coming.