Abstract
A detailed experimental investigation of shock wavelturbulent boundary layer interaction in a supersonic nozzle was carried out using a schlieren visualization and multiple pressure transducers. The chosen Mach numbers at just upstream of shock are 1.37 and 1.60 which show a bifurcated normal shock and a multiple shocks, respectively. The visualization results show nominal variation of shock patterns from a simple normal shock to a pseudo-shock system as increasing flow Mach number. The measurements of wall pressure using multiple transducers and simultaneous sampling method show the propagation of pressure waves caused by shock and boundary layer interaction. In particular, it becomes clear that the upstream moving pressure waves from reattachment point of boundary layer exist in the case of multiple shock case. However, more detailed investigation is required in the case of a single bifurcated shock system.
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