带连续变弯度后缘操纵面机翼的动态失速减缓

主动偏转后缘操纵面可以减小翼型动态失速对气动特性产生的不利影响。研究连续变弯度后缘操纵面在减缓翼型动态失速方面的性能，利用CFD 结合动网格方法，计算NACA 0012 翼型在大幅度俯仰振荡时的非定常气动力；从减缓效果和能量需求两个方面，对比传统刚性操纵面和两种连续变弯度操纵面的动态失速减缓性能。结果表明：当后缘操纵面按正弦脉冲规律偏转时，可以推迟前缘涡的产生，加速后缘涡的发展，降低压力分布在后缘的峰值，进而减小动态失速时翼型的低头力矩极值；后缘操纵面的弯度构型会影响减缓效果，在相同的偏转策略下，弯度描述函数为2 阶多项式的连续变弯度操纵面的减缓效果最好，且能量需求最小。

Alleviation of Dynamic Stall Moments by Morphing Flap

This study set out to investigate the performance of morphing flap on dynamic stall alleviation. The unsteady flow field around the sinusoidally oscillating NACA 0012 airfoil are simulated by computational fluid dynamics (CFD) and dynamic mesh method. Two morphing flaps are compared with the rigid plain flap in terms of control effect and energy consumption. The numerical results show that, when the pulse signal of a sinusoidal shape is used, the flap deflection may be delay the formation of leading-edge vortex (LEV) and accelerate the development of the trailing-edge vortex (TEV). Meanwhile, the peak value of pressure distribution on the trailing-edge is reduced, and the large negative pitching moments are also decreased. The 2nd order morphing flap proposed in this paper could reduce the large negative pitching moment with the least energy requirement.