Prediction of flow field for a 2-D mixed compression supersonic inlet

Abstract

Reynolds Averaged Navier Stokes (RANS) CFD simulation have been carried out over 2-D Axi-symmetric mixed compression supersonic inlet configuration using K-Omega turbulence model for Mach numbers ranging from 2 to 4. The coefficient of pressure, Shock location and variation of pressure and density have been extracted and compared for all the Mach numbers. The oblique shock formation is observed in both the first ramp and second ramp for all the Mach numbers, which results in, the increase in pressure and decrease in free stream Mach number. The presence of ramp in the subsonic diffuser, leads to formation of expansion waves that results in the inlet exit flow to remain in supersonic speed.