Comparative performance analysis of supersonic inlets at various Mach number.

The basic purpose of the intake is to bring the air required by the engine from free flow to the required condition at the inlet of the compressor with minimal overall pressure loss. The inlet should slow the flow down to subsonic speed before the air reaches the compressor. Good inlets allow manoeuvres into high angles of attack and slide at high speeds without interrupting flow to the compressor. The disruptive flow measure converts inertial forces to viscous forces using numerical indices, which are represented by density (r) time velocity (v) times and viscous force (mu) times. The axisymmetric air intake of an internal compression surface creates an isentropic axisymmetric conic flow and has a zero beginning angle with respect to the free uniform stream's velocity vector. After the conical shock wave that marks the end of the conical flow, the flow slows down and reverses, and the exit cross section (throat) forms a uniform flow parallel to the axis. Steps are formed when an internal shock wave first emerges at the inlet's circular leading edge, and the shock then develops further downstream into a longitudinally curved surface of revolution. As the shock approaches the axis its slope and intensity increase continuously and the flow velocity behind the shock decreases proportionally. This shock wave's formation changes as the supersonic Mach number changes. We are analyzing the step formation at various Mach numbers using analytical software. [ABSTRACT FROM AUTHOR]