Hi,

I'm trying to solve in fluent flow around part of wing (dimensions:3x0.3x0.3) in 3D with Spalart-Allmaras turbulence model. On the velocity inlet I set turbulence intensity to 5% and lenght scale to 0.3. There where no problems with convergetion in small attack angle. For higher angles solution don't converge. Where could be a problem?

Regards, Michal

Hi Mike,

Separation of flow occured (i.e. stall) for the higher angles of attack and it's no longer a steady flow over the wing?

Good luck.

p.s.: An airfoil is not a wing. Also at higher angles of attack, you might want to try the SST k-w turbulence model.