Numerical Analysis of Supersonic Axisymmetric Inlet with Single Ramp

Abstract

A computational fluid dynamic analysis on axisymmetric inlet has been performed, to investigate the flow properties of a ram jet engine with a conical inlet. This paper describes about the analysis of different conical inlets with varying semi-vertex angles, angle of attack (AOA) and Mach numbers. Results have shown that as the angle of attack increases, the static pressure ratio decreases, for the constant semi-vertex angle, the static pressure ratio increases with increase in Mach number, as the semi-vertex angle increases, the static pressure ratio increases. It is observed that a pressure recovery of 96% can be achieved for a free-stream Mach number of 1.5 with angle of attack of 0° for 10° cone angle and 98.5% can be achieved for 15° cone angle.