Exit Total pressure condition
 

All,

In many turbomachinery calculations, it is desirable to fix exactly the pressure ratio across the machine. So, I was wondering if it is possible to code up a subsonic exit boundary condition that sets a specified total pressure.

I understand that such a condition may not be physically met with. But is it mathematically a well posed bc ? I have never seen this anywhere
and so perhaps it is not. The usual subsonic exit bc fixes the static pressure on the boundary from which the total pressure is inferred.

Thanks

Sam