为改善气动弹片在小攻角范围内破坏翼型上表面流体附壁的现象，以NACA0018翼型为研究对象，通过数值模拟分析分段式气动弹片对翼型气动性能的影响。结果表明：等比例分段式气动弹片翼型吸力面压力显著降低，升阻比较原始翼型最大提高25.65%；在一定范围内弹片所分段数越多，气动性能改善效果越明显；弹片抬起角度大于14°时会在其下表面形成大涡区，进而对翼型气动性能产生负面影响。

In this paper a segmented elastic flap with equal distance is proposed to improve the phenomenon that the elastic flap destroys the wall attachment of the fluid on the upper surface within the range of small AOAs.With the NACA0018 airfoil as the research subject,the influence of the segmented elastic flap on the aerodynamic performance of airfoil is investigated through the method of numerical simulation.The results show that the suction surface pressure of the equal ratio segmented elastic flap airfoil is significantly reduced,and the liftdrag ratio is increased up to 25.65% compared with the clean airfoil.Moreover,the more the elastic flap is segmented in a certain range,the more evident the aerodynamic performance is improved.However,when the lifting angle of the flap is over 14°,a large vorticity area is formed on its lower surface,negatively affecting the aerodynamic performance of the airfoil.

TK83

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