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[Les Bar]

Hello, I am trying to simulate the supersonic air intake of an aircraft 2D with respect to different mach numbers. Boundary conditions of my project are pressure far-field and pressure outlet and idea gas law and Sutherland viscosity are using. In Farfield BC i need to enter gauge pressure and thermal value of the Mach number but I don't know which relation to calculate it. Could you please help me about it ?

[Federico]

Hello, 

this looks like a duplicate post.

We will see to answer you in your original post: Supersonic Intake Mach-Pressure Relation (ansys.com)

[Les Bar]

Yes, I shared twice. I am waiting for your answer, thank you.