2337 極超音速機のコーナー部での衝撃波/境界層干渉に関する実験的研究(S46-1 圧縮性流れの基礎と応用(超音速流1),S46圧縮性流れの基礎と応用)  [in Japanese] 2337 Experimental Study on Shock Wave/Boundary Layer Interaction around Corners of Hypersonic Planes  [in Japanese]

Experimenrtal study is conducted on the effect of corner angle on the scale of upstream influence in the shock wave/boundary layer interaction flow field on a two-dimensional corner model. Flow visualizations using schlieren and glow discharge techniques are performed in a hypersonic gun tunnel at Mach number 10 and Reynolds number based on the chord length 2.1×10^5. The corner angles studied are in the range from 10°to 30°at intervals 2°. The scale of upstream influence shows a characteristic increase with increasing corner angle.