[antonio_ing]

hi everybody

I'm still trying to simulate the flow around a naca 0015 with the simpleFoam solver and the SpalartAllmaras turbulence model. Now i can finally compute the pressure coefficient at the airfoil surface so a big step is done :-)

However, there is something strange in the pressure coefficient since the minimum value is lower than the xfoil's one (absolute value of course), denoting a clear separation (Cp almost constant) and also without satisfying the Kutta condition (i.e. there is no clear pressure recovery).

The nu=1e-5 m^2/s and U=100 m/s and c=0.1m so the Re=1e6 (quite high).

I have tried to change the ratio between nut and nuTilda and the boundary layer thinned a little but not so much. Should I go further in this direction? should I change the grid? should I change my job? :-)

Thanks in advance

[antonio_ing]

should I change maybe the grid close to the profile surface to increase the sink term in the spalart-allmaras model?