National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Fluid Science Research Group
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所資料
雑誌名(英)
Technical Memorandum of National Aerospace Laboratory
Experiments on attachment line transition of two yawed cylinder models with a sharp and a hemisphere nose were conducted in a hypersonic wind tunnel. The tests were conducted at a free-stream Mach number of 7.1, free-stream Reynolds number based on cylinder diameter varying from 0.1 x 10(exp 6) to 1.3 x 10(exp 6) and angles of attack of 30 deg, 40 deg and 50 deg. Results for the sharp nose model tests matched those of other hypersonic wind tunnel tests. Tests for the hemisphere nose model at alpha = 30 deg showed nose bluntness to have a greater effect on transition than expected, based on the entropy layer swallowing effect, while at alpha = 50 deg, the effect was close to that expected. The bluntness effect at an angle of attack of 40 deg showed the opposite tendency to the other cases.
極超音速流中斜円柱付着線上境界層遷移への鈍頭度の効果に関する実験
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