半角7°圆锥马赫数6边界层转捩的自由飞实验

在气动物理靶上开展了半角7°圆锥的边界层转捩测量实验，模型材料为铝合金，表面采用氧化发黑处理或涂覆低热导率涂层，底径33mm，球头半径0.27~2.50mm，马赫数4.89~6.63，单位雷诺数4.8×107/m~5.2×107/m，总迎角0.8°~5.8°，采用阴影和红外辐射成像获得了模型边界层图像和转捩阵面形貌，测得转捩雷诺数介于2.4×106~5.6×106之间.结果表明:转捩雷诺数随迎角增大而减小；一定的球头钝化可以推迟转捩。

Free flight experiment on boundary layer transition of 7° half angle cone at Mach 6

A series of boundary layer transition measurements of the 7° half angle cone at Mach 6 in the Aero-physic Range were conducted. The models are made of aluminum alloy with black oxidation or low thermal conductivity coating. The base diameter of the cone is 33mm, and the radius of the nose tip is among 0.27~2.50mm. The parameter covers Mach number 4.89~6.63, Unit Reynolds number 4.8×107/m~5.2×107/m, and the total angle of attack 0.8°~5.8°. The boundary layer shadowgraph and surface inferred images which reflect the transition line configuration were obtained, and the transition Reynolds number was calculated to be 2.4×106~5.6×106. The results indicate that:the transition Reynolds number decreases by enlarging the angle of attack, certain nose tip scale would delay the transition.