極超音速飛翔体に生じる後流の放電発光法による可視化
1997 年 45 巻 524 号 p. 527-532
詳細
1997 年 45 巻 524 号 p. 527-532
Investigations of the wake behind a hypersonic vehicle have been made by visualizing the flow field around the hypersonic vehicle. In order to visualize the flow field, the electric discharge method is utilized. In these experiments, visualizations of a stream line, shock shapes, a temperature field, and a boundary layer around the hypersonic vehicle have been performed by the electric discharge method. These experiments are carried out by using a hypersonic shock tunnel. The characteristics of the tunnel are the Mach number is 10 and the duration is 10m·s.
