Study on the Injection Cooling Method for Hypersonic Flow over Flat Plate with Tile Gaps

Abstract

In this paper, an active cooling method for an array of tiles laid with gaps over the surface of a hypersonic vehicle was proposed and investigated by both the Navier-Stokes analysis and the wind tunnel experiment at Mach number 7 in Kashiwa campus, the University of Tokyo. In this method, the cold air is injected in the upstream direction from a slit set on the wall of the tile gap. The slit is parallel to the surface and is located at the intersection of the lateral and longitudinal gaps. The numerical and experimental results show that the peak heating at the corner of the forward-facing gap wall is successfully suppressed by the injection. The mechanism of the gap heating suppression was clarified in the numerical study by detailed observation of the flow field near the surface and in the cavity.