Matching Effects of Supersonic Inlet for Integral Rocket Ramjet Engine Applications

The mathematical model of the integral solid propellant rocket ramjet engine with two-dimensional supersonic inlet is presented. Selections of different design points for the supersonic inlet are made. The altitude characteristics and velocity characteristics of the engine are given. Matching effects of the supersonic inlet for integral rocket ramjet engine are obtained. The numerical results show that different inlet design points have remarkable effects on both inlet aerodynamic stability margin and the engine performances. Deliberate considerations for supersonic inlet design should be made during application of supersonic inlet for integral rocket ramjet engines.