two dimensional supersonic ramjet inlet model
 

Nowadays, i am trying to validate my analytical results that are obtained using shock relations and one dimensional gas equations for supersonic two dimensional ramjet inlet with two compression surfaces. Here is the my solution strategies; I have big enough domain to choose pressure farfield BC for the inlet.(3.5 mach and 10353Pa at 16km altitude) There exists very high back pressure at the entrance of the combustion chamber (about 450000Pa), so i defined there as a constant pressure outlet BC. Unfortunately, fluent ignores that value so, terminal normal shock does not occur at the throat section or elsewhere in the subsonic diffuser. During my analysis, i get two different results: normal shock goes out of the inlet throat and solution diverges, or ignoring the back pressure, normal shock is not captured. Are there anyone who analyse 2_D ramjet diffuser using fluent or who can help me about my problem?

Thanks...

When the normal shock moves out of the inlet, it implies that the back pressure isn't high enough. You will have to raise the back pressure.