Shock-induced leading-edge separation in hypersonic flows

We investigate the leading-edge separation, also called negligible boundary-layer thickness induced by an impinging shock on a sharp flat plate. The canonical wave/boundary-layer interaction configuration consisting of wedge and plate wall, placed in hypersonic free stream, is used for investigations. first construct theoretical model separated flow field (LESF) which predicts separation bubble geometry surface pressure distribution as function three parameters: free-stream Mach number, angle reattached turning angle. Markedly different predictions are obtained oblique near normal reattachment surface. Experiments tunnel at nominal $6$ flow, with generated $26.6^{\circ }$ , to validate model. Schlieren visualization using high-speed camera measurements fast response piezoelectric sensors diagnostics employed. For range impingement locations, LESFs observed be geometrically similar good agreement LESF When location gets closer leading edge, it from experiments that no longer similar, increases edge beyond similarity. work thereby offers elaborate description when occurs edge.