THEORETICAL AND EXPERIMENTAL STUDIES OF THE SHOCK WAVE-BOUNDARY LAYER INTERACTION ON COMPRESSION SURFACES IN HYPERSONIC FLOW

摘要: Abstract : A detailed description is given of the theoretical and experimental studies shock wave-laminar boundary layer interaction on curved compression surfaces in hypersonic flow. Integral forms equations were used for conservation mass, streamwise momentum, normal moment momentum energy to describe development attached separated layers a curve surface. In study, skin friction, heat transfer pressure measurements made series flat plate-cylindrical arc-wedge surfaces. Pitot cone above surface separation reattachment regions flows estimate static difference across layer. The radius curvature cylindrical arc, inclination wedge, unit Reynolds number free-stream varied examine their effect properties both over models.