compressible flow in a duct - supersonic inlet mach number
 

Dear All.... I have tried out the simulation of compressible flow (Mach=3) through a constant area duct (both 2D and 3D) in fluent . But i could not able to predict the variations properly (shock wave reflections). Can you please suggest how to predict and what turbulence model I should use for the analysis. (I tried with inviscid initially). I used pressure inlet and pressure outlet BCs. Help me the exact calculation method for these BCs.

Hey,

there is a good tutorial about compressive flow in Fluent (Tutorial 4 : Modeling Transient Compressible Flow)

Sincerly

Adrien

Dear ,
Are u expert in combustion with fluent

Nope, sorry

BC's Needed for Supersonic flow through a duct
 

thanks a lot Mr. Adrien...

I have tried the way as given in the fluent tutorial. But still not able to capture the shock wave reflections.. Can you please let me know the settings for the inlet and outlet BC's.

Thanks and Regards,

Chandrabose

no am not an expert n combustion ..