An Experimental Study of Flexible Membrane Airfoils at Low Reynolds Numbers
An Experimental Study of Flexible Membrane Airfoils at Low Reynolds Numbers
复制标题
低雷诺数柔性膜翼型件的实验研究
DOI：
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发表时间：
2007
期刊：
影响因子：
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通讯作者：
Hui Hu
中科院分区：
文献类型：
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作者：
M. Tamai;Jeffery T. Murphy;Hui Hu
一项实验研究探讨了在低雷诺数下使用柔性膜翼型/机翼对MAV应用的好处。除了测量作用在柔性膜型/机翼上的气动力外，还利用高分辨率粒子图像测速（PIV）系统进行了流场测量，以量化不同迎角下柔性膜型/机翼周围旋涡和湍流结构的瞬态行为。力测量结果表明，在低雷诺数下，柔性膜翼型比刚性膜翼型具有更好的气动性能。柔性（或刚性）的膜皮肤被发现影响气动性能的膜翼型显著。PIV测量表明，柔性膜翼型可以自动改变其弧度（即截面形状），以适应来流，以平衡不同迎角时应用于翼型上下表面的压力差，从而抑制膜翼型上的流动分离。柔性膜翼型的变形也降低了翼型的有效迎角，从而延缓了翼型失速。
An experimental study was conducted to explore the benefits of using flexible membrane airfoils/wings at low Reynolds numbers for MAV applications. In addition to measuring aerodynamic forces acting on the flexible membrane airfoils/wings, a high-resolution Particle Image Velocimetry (PIV) system was used to conduct flow field measurements to quantify the transient behavior of vortex and turbulent flow structures around the flexible membrane airfoils/wings at different angles of attack. The force measurement results revealed that flexible membrane airfoils can provide better aerodynamic performance compared with their rigid counterpart at low Reynolds numbers. The flexibility (or rigidity) of the membrane skins was found to affect the aerodynamic performance of the membrane airfoils significantly. The PIV measurements elucidated that flexible membrane airfoils changed their camber (i.e., cross sectional shape) automatically to adapt incoming flows to balance the pressure differences applied on the upper and lower surfaces of the airfoils at different angles of attack, thereby suppressing flow separation on the membrane airfoils. The deformation of the flexible membrane airfoils also reduced the effective angle of attack of the airfoils to delay airfoil stall.