側壁圧縮型極超音速インレットの内部流れ場に関する実験的研究
1994 年 42 巻 484 号 p. 300-308
詳細
1994 年 42 巻 484 号 p. 300-308
Sidewall compression type inlet models for the Scramjet engine were tested in NAL's hypersonic wind tunnel at Mach 7.1. Its contraction ratio, sweep angle, entrance Mach number and cowl size were set in variable manner along the experimental plan. The inlets were investigated with the flow visualization and pressure measurement techniques. As results, without the sweep angle the pressure near the open side was less than near the body side due to the spill from the inlet. It had agreement with the 2-dimensional calculation near the body only. With the sweep angle 45 degree, the lower pressure region due to the spill became small and the performance was higher. The some kinds of the flow field in the inlet owing to the variation of the configuration and basic data of the sidewall compression type inlet were obtained.
