極超音速圧縮コーナー流の可視化 Visualization of Velocity Fields around Hypersonic Compression Corner Flows
Understanding of hypersonic viscous interaction phenomenon over control surfaces and engine intakes is of particular importance for designers of hypersonic vehicles. However, experimental data of velocity fields around the compression corner which is an idealized configuration of these practical situations are sparse chiefly because it is difficult to obtain such data owing to short duration, high velocity, and rarefaction of the test flow in hypersonic ground facilities. In this report, we shall try to apply the high frequency impulsive glow discharge technique to obtaining the hypersonic velocity fields. The experiment is carried out in a hypersonic gun tunnel at Mach number 10 and Reynolds number based on the frontal plate chord length 2.8×10<SUP>5</SUP>. Time lines are obtained successfully, even for separated flow cases.
- 可視化情報学会誌. Suppl.
可視化情報学会誌. Suppl. 24(2), 83-84, 2004-09-15