SUPERSONIC AIR INLET FOR A HIGH VELOCITY PROPULSION SYSTEM

Abstract

The paper aims to determine the optimal geometry, the control law and the operational limits of a supersonic air inlet; its operation control consists of its central cone positioning, with respect to the flight Mach number, keeping in sight the necessity of a suitable parameters’ distribution into engine’s combustion chamber. Inlet’s optimal architecture shall be determined (based on an algorithm regarding the maximization of the total pressure recovery), using basic planar geometry principles. Based on the optimal geometry of the inlet, its flow rate characteristic and its control law, as well as inlet’s operation limits were calculated and graphically represented.