Free flight experiment on boundary layer transition of 7° half angle cone at Mach 6
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摘要: 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。Abstract: 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.
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图 5 实验ZL03模型水平方向阴影图像(俯仰角5.0°，侧滑角2.9°)
Figure 5. Horizontal shadowgraph of test ZL03 (pitch angle 5.0°, yaw angle 2.9°)
图 6 实验ZL03模型阴影图像两侧轮廓线上的涡尺度分布
Figure 6. Periodic scale distribution on both sides of the shadowgraph of test ZL03
图 8 实验ZL07模型水平方向阴影图像(俯仰角0.6°, 侧滑角2.0°)
Figure 8. Horizontal shadowgraph of test ZL07 (pitch angle 0.6°, yaw angle 2.0°)
图 9 实验ZL07模型阴影图像两侧轮廓线上的涡尺度分布
Figure 9. Periodic scale distribution on both sides of the shadowgraph of test ZL07
图 12 不同迎角下模型迎、背风侧转捩雷诺数对比
Figure 12. Transition Reynolds number comparison under different conditions
表 1 弹道靶转捩实验状态参数表
Table 1. Test conditions
No. Φ/mm L/mm R/mm Ra/μm v/(km·s-1) p/kPa T/℃ Ma Re/L/(107m-1) Re/106 ZL03 32.91 130.63 0.46 0.88 1.70 44.34 27.6 4.89 4.82 6.30 ZL04 32.89 130.69 0.45 0.88 2.05 37.40 24.9 5.92 4.95 6.47 ZL05 32.93 132.66 0.27 0.88 2.17 37.06 25.0 6.27 5.19 6.88 ZL07* 32.95 127.29 0.99 4.78 2.18 37.09 27.3 6.27 5.18 6.59 ZL08 32.92 132.51 0.30 0.88 2.29 32.30 23.3 6.63 4.80 6.36 ZL09 32.82 116.60 2.50 0.88 2.08 37.70 23.2 6.03 5.09 5.94 ZL10* 32.92 130.69 0.45 1.56 2.15 37.72 28.0 6.18 5.18 6.77 注：Φ为模型底径，L为模型长度，R为模型球头半径，Ra为模型表面粗糙度均值，v为模型飞行速度，p为靶室压力，T为靶室温度，Re/L为单位雷诺数，Re为模型雷诺数，标记*的实验模型表面为低热导率涂层。 
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表 2 弹道靶转捩实验测量结果
Table 2. Test result of ballistic range transition measurement
No. R/mm Ma Re/L/(107m-1) 球头雷诺数/104 俯仰角/(°) 侧滑角/(°) 迎角/(°) 转捩距离/mm 转捩雷诺数/106 迎风侧 背风侧 迎风侧 背风侧 ZL03 0.46 4.89 4.82 4.43 5.0 2.9 5.8 50 60 2.41 2.89 ZL04 0.45 5.92 4.95 4.45 0.8 0.2 0.8 104 113 5.16 5.60 ZL05 0.27 6.27 5.19 2.80 -2.2 0.0 2.2 83 74 4.30 3.85 ZL07 0.99 6.27 5.18 10.30 0.6 2.0 2.1 79 82 4.10 4.25 ZL08 0.30 6.63 4.80 2.88 -0.7 1.7 1.8 86 114 4.12 5.46 ZL09 2.50 6.03 5.09 25.50 -1.2 0.8 1.4 未转捩 未转捩 未转捩 未转捩 ZL10 0.45 6.18 5.18 4.66 -0.6 4.9 4.9 63 57 3.28 2.96
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