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

Usman, can we see your CFD domain? Try to put a upper of lower wall (depends on the CFD domain) as INLET [with the aim to make sure that all the "inlet" vector of velocity, touches the airfoil), the other wall as opening (Also, I would try another simulation as wall free slip and compare results) and the outlet, leave it like outlet.

What turbulence model are you using? Turbulence models some times are not rubust and present some convergence problems.

What is your y+ ?

Are you having convergence of expressions like the Cd o Cl ?

How is your mesh quality? topology?

Cheers, Santiago