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.
CFD simulations have been carried out to investigate turbulent compressible flow over various payload fairing configurations at zero incidence in the Mach number range of 0.6-1.5 and Reynolds number range of 9.5x10 6-12.1x10 6. The Spalart-Allamaras model has been used to solve a modeled transport equation for the kinematic eddy (turbulent) viscosity. The presence of transonic shock clearly seen for Mach numbers above 0.6. The supersonic region increases with increasing free stream Mach number and the terminal shock moves downstream towards boattail. The flow separates near the cylinder-boattail junction and forms a recirculating region of relatively low velocity for Mach numbers above 0.6. The coefficient of pressure, 'C p ', coefficient of skin friction, 'C f ', shock location, separation length and pressure rise due to shock and reattachment have been extracted and compared.
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