Exit Total pressure condition
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.
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