Abstract
An experimental study has been conducted to investigate the flow physics along a three-dimensional contour bump in a Mach 1.3 supersonic free-stream. Monochrome Schlieren photography technique was employed for flow diagnostics. Results obtained from the experimental study indicated that the flow pattern appears over the bump upper surface depends on the shock impingement location. It was observed that two lambda shock structures were formed over the bump upper surface in both cases being studied. It was observed that when the normal shock is impinged at the bump crest, the flow downstream of the bump crest remains relatively attached while separated flow appeared downstream of the bump crest for all other normal shock impingement locations.
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