The reattachment zone structure of a supersonic separated ramp flow was experimentally studied at M∞ = 6. Several ramp model configurations with and without side walls were considered. It was found that the geometric size of streamwise vortices in the reattachment zone increases due to the absence of transverse flow in the separation region. Moreover, flow separation regions were detected on the model side walls which interact with the ramp-induced separation region, forming corner vortex structures.
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.
This article presents the study results for heat transfer in supersonic laminar separated compression corner flow. The study was carried out for free-stream Mach number M = 6 and the compression ramp angle in the range of φ = 20° – 40°.
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