Hi there!

It happens that when I try to solve the inviscid incompressible flow around a 2D airfoil set at high angle of attack (say ~ 25 degrees) the solution shows a sort of ficticius separated boundary layer on upper surface or, if one prefers, there is no Kutta condition verified at trailing edge. Can anyone help me with this? Any suggestion on how I can obtain a solution similar to that coming from panel methods where the Kutta condition is explicitly imposed so that the solution does not depend on the value of angle of attack chosen?

Many Thanks

Ferdinando

Dear Ferdinando Inviscid model refer to that fluid assume with no friction or shear stress, Kutta applied for non invisicd flow, try to make your model as turbulence or laminar (depend to reynold number)

Yes, Chandra is right. This is not supposed to work! There is no point in trying to do high angle of attack calculations of an incompressible inviscid fluid. It doesn't exist, and if it gave the same answer for this as the panel code I would be really worried about Fluent.