23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-2.9.3

DESIGN METHOD FOR PROBLEMS INVOLVING SHOCK BOUNDARY-LAYER INTERACTION

A. G. T. Cross
BAE Systems, UK

Keywords: supersonic flow, shock boundary layer interaction

Three-dimensional boundary layer theory is applied to the air inlet studied by GARTEUR Action Group 34. The essential feature is a stream surface passing through a conical shock. Boundary layer condition at the shock is largely determined by the attitude of incoming inviscid flow to the surface projection of the shock.

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