一种前后缘连续变弯度翼型气动特性分析

Analysis on the aerodynamic characteristics of continuous variable camber morphing airfoils of leading and trailing edge

提出了一种基于厚度不变的翼型前后缘连续偏转变形规律,并以NACA0015翼型为例,实现了翼型变弯度的参数化。以柔性伸缩蒙皮支撑结构和机械结构实现了可连续光滑偏转后缘的变弯度翼型,验证了变形规律。以前后缘偏转角度为参数,计算并分析了各个变形状态下翼型扰流流场和气动特性,讨论了变形参数对气动特性的影响,研究了气动特性的产生机理。研究结果表明:在大迎角下,前缘偏转角对翼型失速有一定的抑制作用;在中小迎角范围内,翼型升阻比随着后缘偏转角的增大而增大,且不论迎角如何变化,总可以通过前后缘偏转来获得较高的升阻比。

First of all, a novel morphing law of leading and trailing edge variable camber was brought out and carried out on airfoil NACA 0015. Meanwhile, variable camber airfoil with continuous smooth mor- phing leading and trailing edge was realized using shape memory polymer flexible skin and mechanical structures to validate the morphing law. Flow structure and aerodynamics was analyzed based on morphing parameters, which are deflection angles of 1 rameters on aerodynamic characteristics was characteristics was studied. It is shown that eading and trailing edges. Also the impact of morphing pa- discussed and the formation mechanism of the aerodynamic at large angles of attack, leading edge deflection angles in- crease the stalling angles of attack. At small angles of attack, lift-to-drag ratios increase with increasing trailing edge deflection angles. And lift-to-drag ratios can be increased by selecting proper leading and trailing deflection angles.