Abstract

It has been proposed that passive boundary layer control technology could be applied to the problem of reducing the supersonic intake total pressure losses associated with the intake shock wave/boundary layer interaction. This paper reports the results of a numerical investigation of a possible realisation of this idea. The passive bleed geometry tested had a wide suction slot inside the intake duct and a narrow tangential injection slot upstream of the intake entry, the slots being interconnected by a breather passage. Experiments have been conducted with a threedimensional intake model in a small supersonic tunnel at a Mach number of 1.36 and computational fluid dynamics calculations have been performed for a similar geometry, but reduced to two dimensions, in an effort to confirm the experimental results in the absence of the side-wall boundary layers. The results show that passive control can reduce the shock interaction losses at off design conditions. However, at intake design conditions the predicted total pressure losses increase. More work is necessary to determine the best passive control configuration. Notation

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