Abstract
The aim of this work is to study the attainable velocities for a supersonic diffuser. Numerical analysis is carried out to identify the supersonic characteristics. The deceleration of air from free stream supersonic velocities in the 2D channel has been studied and analysed at a specific altitude. Ramp instalment maximizes the total pressure recovery. The geometry is generated in CATIA software and 2-D flow numerical simulation is done using ANSYS-CFD V15.0. Flow analysis is done by keeping the altitude constant and varying the inlet Mach number. A comprehensive study from the analysis provides the range in which Mach number at the inlet can be varied for a supersonic aircraft. The obtained flow phenomena in the supersonic diffuser domain are reported with the help of Mach number, static pressure, and velocity plots.
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