Pressure Far-Field BC
 

Hi all,

I'm trying to simulate flow over an airfoil. I'm currently using an O-mesh with pressure far-field BC's. The downstream boundary is about 20 chords away from the airfoil. The Mach number is 0.05. The solution diverges as soon as I start the calculation. I've tried two different methods : 1) I set operating pressure to zero and freestream static pressure to be 101325 Pa. 2) I set operating pressure to be 101325 and freestream static pressure to be 0. However, both of these don't seem to work, and the solution diverges in either case. I'm not sure what I'm doing wrong over here. Does anyone have any ideas?

Thanks,
Prasad

There is a tutorial on a airfoil in fluent documentation is that the one you use ??

That's right. The only difference is that my Mach number's smaller.