グロー放電トレーサー法を用いた極超音速圧縮コーナー流の研究

概要

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In this report, we apply high frequency impulsive glow discharge technique for obtaining the flow pattern upstream of a compression corner. For purpose of comparison, schlieren visualization using high speed video camera is also performed. These experiments are carried out in a hypersonic gun tunnel at Mach number 10 and Reynolds number based on the frontal plate chord length 2.1×105. The corner angles studied are in the range from 0 to 30deg at zero incidence. Time lines are obtained successfully even for separated flow cases and the boundary layer edges visualized by the discharge-tracer technique correlate well with those defined through the schlieren images. The extent of the upstream influence becomes large with increasing corner angles and the separated boundary layer is transitional to turbulent flow for the largest angle case tested. Free interaction similarity using Newtonian theory is presented and it seems reasonable with respect to the present experimental results.
社団法人日本航空宇宙学会の論文
2006-08-05