Hi all

i am calculating a supersonic problem, but now i don't know how to set the supersonic inlet boundary conditions.

eager for some help. thx in advance.

Pl. see library case B529 in PHOENICS

Vikas

I had read the library in fact but I think those libraries don't fit for my problem. those problems know the inlet mach number and temperature, so the velocity can be calculated. but my problem should calculate the velocity according the inner pressure. so the velocity varies with the iteration number untill it reaches the steady solutions. if anybody know how to handle it, please help me.

thanks in advance.