[ryan_m]

Hi,

Im running 3D airfoils (NACA 0016 @ 0 degrees) using an incompressible solver (simpleFoam). The results Im getting aren't making much sense: non-symmetrical pressure distribution, the velocity at the inlet seems to be different to what I specified. I think my boundary conditions are at fault. Could someone please have a look at the following boundary conditions to see if there are any errors:

Pressure: fixedValue outlet, zeroGradient elsewhere

Velocity: fixedValue inlet, zeroGradient outlet, movingWallVelocity on boundaries and 0 at the airfoil walls

k, epsilon, nuTilda: fixedValue inlet, zeroGradient elesewhere

Any help will be much appreciated.

Ryan