[leo_NM]

Good night

I'm doing some inviscid simulations over a NACA 0012 at 4º (angle of attack) and M 0,7. What I'm facing is a kind of viscous effect in the NACA surface.

The convergence is not good as well. 10^-3 for all the residuals after 5000 iterations. I tried to re-do the mesh but the problem with convergence still there. The setup of the problem is:

BC - Pressure Farfield - 67767 Pa - 273,3 K - M=0.7
CFL - 0.5
Second Order upwind - green gauss node based.

The mesh has some refinement over the airfoil (0.0002 airfoil -> first layer).

From my point of view this kind of effect shouldn't be happening in inviscid simulation.

Is this normal for FLUENT ?
What should I do to get better convergence ?

thanks.