Development and interaction of vortices over a very low aspect-ratio wing under pitch-up motion
Development and interaction of vortices over a very low aspect-ratio wing under pitch-up motion
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上仰运动下极低展弦比机翼上涡流的发展和相互作用
DOI：
10.1017/jfm.2022.451
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发表时间：
2022
影响因子：
3.7
通讯作者：
Dong L
中科院分区：
文献类型：
--
作者：
Dong L
在有效雷诺数为的风洞中，对0.277小展弦比矩形薄机翼的涡结构进行了研究。在弦中点作上仰运动时，最大升力角随俯仰速率的增大而增大，但最大升力系数减小。俯仰运动也引起机翼上方涡的发展延迟，这种延迟随着俯仰速率的增加而增加。俯仰运动引起的前缘涡发展的延迟与翼尖涡发展的延迟几乎相同，表明前缘涡的动态特性受到翼尖涡的强烈影响。粒子图像测速测量证实了这一点，表明在俯仰运动过程中，小展弦比机翼上的翼尖涡诱导了强烈的下洗，影响了前缘涡的发展，从而导致了流动分离的延迟。
The vortical structures over a thin rectangular wing with a very low aspect ratio of 0.277 were investigated in a wind tunnel at an effective Reynolds number of . When applying pitch-up motion pivoted at mid-chord, the maximum lift angle was increased with an increase in the pitch rate, but the maximum lift coefficient was reduced. The pitching motion also caused delay in the vortical development over the wing, which was increased with an increase in the pitch rate. The delay in the leading-edge vortex development due to the pitching motion was nearly identical to that in the tip vortex development, indicating that the dynamics of the leading-edge vortex was strongly influenced by the tip vortex. This was confirmed by particle image velocimetry measurements, which demonstrated that the tip vortex over a very low aspect-ratio wing induced strong downwash to influence the development of the leading-edge vortex during the pitching motion, which led to a delay in flow separation.