通过研究尾缘气动弹片对翼型动态失速特性影响，提出一种基于气动弹片的主动控制策略，使其于大攻角时抬起，小攻角时闭合。并采用计算流体动力学方法对比分析主动式气动弹片对不同厚度翼型抑制流动分离作用的效果。结果表明：对于薄翼型，发生动态失速时，气动弹片可延缓翼型尾缘涡旋与前缘主流涡的相互作用，减小翼型升力系数骤降幅度；随翼型厚度增加，流动分离点从翼型前缘转向后缘，气动弹片可有效分割较大分离涡，减轻流动分离程度，限制分离涡发展，同时抑制尾缘伴随小涡产生，提高翼型升阻比。

Through studying the influence of trailing edge aerodynamic flap on dynamic stall characteristics of airfoils,an active control strategy based on aerodynamic flap was proposed to make it lift at large angle of attack and close at small angle of attack.The computational fluid dynamics (CFD) method was used to contrastively analyze the effect of active aerodynamic flap on the flow separation inhibited by airfoils with different thicknesses.The results show that when dynamic stall occurs,the aerodynamic flap of thin airfoil can delay the interaction between airfoil trailing edge vortex and leading edge mainstream vortex,and reduce the sudden drop range of lift force coefficient of airfoil.With the increase of airfoil thickness,the flow separation point turns from the airfoil leading edge to the trailing edge.The aerodynamic flap can effectively segment larger separation vortexes,reduce the degree of flow separation,limit the development of separation vortexes,and at the same time inhibit the generation of accompanying small vortexes at the trailing edge,thus increasing the liftdrag ratio of the airfoil.

TK83

国家自然科学基金（51976131，51676131）；上海“科技创新行动计划”地方院校能力建设项目（19060502200）