REDUCTION OF SHOCK-INDUCED BOUNDARY-LAYER SEPARATION IN HYPERSONIC INLETS USING BLEED

The proper design of the inlet system is of great importance for the p erformance of air-breathing hypersonic space planes. One of the domina ting flow phenomena inside such a hypersonic inlet is the mutual inter action of oblique shocks with boundary layers, forcing the boundary la yer to separate from the inlet wall. As a method to improve the inlet efficiency, the application of bleed is examined using a generic Aat p late model and a single shock/laminar boundary layer interaction. By m eans of computational fluid dynamics as well as experiments in the hyp ersonic wind tunnel facility H2K of the DLR, favourable design paramet ers for the bleed set-up are presented and the efficiency of bleed for the reduction of the boundary layer separation and the thermal loads on the surface is demonstrated. (C) Elsevier, Paris.