The effect of aspect ratio and angle of attack on wing-plate junction flow
收藏doi.org2025-03-25 收录
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http://doi.org/10.17632/b39sxdbtpx.1
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The mean pressure of the flow field formed within wing-body junctions are presented. Wings formed from constant-chord, NACA 0012 airfoil sections were used, with aspect ratios of 0.2 and 1.0 and angles of attack of 0, 5 and 10 degree.
本数据集展示了在机翼-机身交汇处形成的流动场中平均压力的分布情况。实验中采用了常弦长度的 NACA 0012 气动剖形翼片，其翼型比分别为 0.2 和 1.0，攻角分别为 0 度、5 度和 10 度。
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