[giammy92]

Hi guys, I have a flux on an airfoil 2D inclined of 13° and i have obtained a good cl compared with experimental results but cd very high of about 0.07 compared to 0.02-0.03. I have also too high residual for p, after 20000 iterations Initial residual = 0.0709856.
Where can i find my error? I'm asking to me if i've gave right bc for pressure on trailing edge, because there is separation but i set zeroGradient like for all airfoil. Have i to set another bc for trailing edge?
Other considerations?