On the performance of a body integrated diverterless supersonic inlet

Abstract

Extensive experimental investigations on a body integrated Diverterless Supersonic Inlet (DSI) were conducted. These inlets are implemented for both supersonic flow compression and boundary layer diversion using a three-dimensional bump in combination with a suitable cowl lip. Experiments were performed at a free stream Mach number of 1.65, the design Mach number, and at zero degrees angle of attack and zero degrees sideslip angle. To recreate the operational conditions more accurately and have a realistic performance characteristic, the intake was integrated with a fuselage and a forebody nose with an elliptical cross-section. Wind tunnel tests were conducted at critical, subcritical and supercritical operating conditions where DSI operates in its stable states. The results showed that the present DSI had acceptable performance characteristics in the stable operating conditions and provides the required mass flow and static pressure compression ratio. In addition, it has a wide stable subcritical operating condition. Moreover, a relatively different behavior in the DSI performance curve is evident due to its body integrated geometry and 3D configuration of the bump and cowl lip, especially in the supercritical conditions.