[vietle]

Hello, I have these gases flow conditions and according to the article I'm currently validating (supersonic combustion model), the inlets are set as pressure inlets, outlet is set as pressure outlet.

But in the table, I see Mach number and only static pressure. And I'm fairly new to this and I don't know how to setup this case. So far I've only try to run it with pressure-far-field but I don't think it was right.

I know I need to have the ratio of specific heat to calculate the total pressure, but the materials and the conditions are kinda insane to me.

How can I setup as pressure inlets with these given BCs. Thanks!

[LoGaL]

it is just air at inlet, nothing burned yet, so you can calculate the total pressure from the static pressure and mach number, using the usual isentropic relations....

https://www.grc.nasa.gov/www/k-12/ai.../isentrop.html