Simulating flow over an airfoil!

Usman

Hi, I am a simulating a flow over an airfoil at 5 deg angle of attack. For that i have set the inlet velocity coordinates to be U=0, V=50sin(5) & W=50cos(5). I have set the upper and lower walls of the wind tunnel as "Opening" with static pressure entrainment. My problem is that i am not being able to achieve convergence. I get following message from solver:

"A wall has been placed at portion(s) of an OUTLET boundary condition (at 48.4% of the faces, 49.1% of the area)to prevent fluid from flowing into the domain". I have also set up my outlet boundry condition as "Opening", but solution does not converge. Any advice on how to fix the problem will be appreciated! Thanks