带 连 续 变 弯 度 后 缘 操 纵 面 机 翼 的 动 态 失 速 减 缓

Active deflection of trailing edge control surface can reduce the adverse effect of airfoil dynamic stall on aerodynamic characteristics. This study set out to investigate the performance of morphing flap on dynamic stall alle- viation. The unsteady flow field around the sinusoidally oscillating NACA 0012 airfoil are simulated by computa- tional 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 sinu- soidal 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 trail- ing-edge is reduced，and the large negative pitching moments are also decreased. The 2nd order morphing flap pro- posed in this paper could reduce the large negative pitching moment with the least energy requirement.