Dynamic layer formation in the reattachment zone for a supersonic laminar separated flow

Abstract

In this work, results of an experimental study of the flow structure in the region of reattachment of a supersonic laminar separated flow are reported. The separated flow is generated by a model shaped as a compression corner consisting of a horizontal flat plate followed by a ramp. The model width is equal to the plate length from the leading edge to the plate/ramp junction line. The ramp angle is varied in the interval φ = 20°–50°. The free-stream Mach number is M_∞ = 6 or 8. The analysis of the Pitot pressure profiles near the ramp wall in the downstream direction behind the reattachment line confirms the existence of a high-pressure layer with the total pressure being appreciably greater than in the surrounding flow.

Keywords

Boundary layer compression corner separation flow shock wave supersonic flow

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