Effects of wing flexibility on aerodynamic performance of an aircraft model
Effects of wing flexibility on aerodynamic performance of an aircraft model
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DOI：
10.1016/j.cja.2021.01.012
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发表时间：
2021-03
影响因子：
5.7
通讯作者：
Qinfeng Guo;Xi He;Zhuoqi Wang;Jinjun Wang
中科院分区：
文献类型：
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作者：
Qinfeng Guo;Xi He;Zhuoqi Wang;Jinjun Wang
为研究机翼柔性对飞机气动性能的影响，在简化的飞机模型上进行了低速风洞实验。在雷诺数为5.4 × 10 ~ 4 ~ 1.1 × 10 ~ 5的范围内，对膜的受力、变形和速度场进行了测量。在升力曲线中，观察到两个峰值。第一个峰值对应于失速，对机翼柔度的敏感性远大于第二个峰值，第二个峰值几乎保持不变。与刚性机翼模型相比，最优情况下失速延迟近5°，相对升力增量约为90%。结果表明，升力增强区对应于较大的变形和较强的振动，从而导致柔性翼面附近较强的流动混合。因此，前缘分离被抑制，并且空气动力性能被显著改善。此外，还讨论了后掠角和雷诺数对柔性机翼气动特性的影响。
The low-speed wind tunnel experiment is carried out on a simplified aircraft model to explore the influence of wing flexibility on the aircraft aerodynamic performance. The investigation involves the measurements of force, membrane deformation and velocity field at Reynolds number of 5.4 × 104–1.1 × 105. In the lift curves, two peaks are observed. The first peak, corresponding to the stall, is sensitive to the wing flexibility much more than the second peak, which nearly keeps constant. For the optimal case, in comparison with the rigid wing model, the delayed stall of nearly 5° is achieved, and the relative lift increment is about 90%. It is revealed that the lift enhanced region corresponds to the larger deformation and stronger vibration, which leads to stronger flow mixing near the flexible wing surface. Thereby, the leading-edge separation is suppressed, and the aerodynamic performance is improved significantly. Furthermore, the effects of sweep angle and Reynolds number on the aerodynamic characteristics of flexible wing are also presented.