为提高风力机叶片翼型气动性能，在NACA0018翼型上表面附加类似于鸟类羽毛的弹片，通过数值模拟方法研究弹片参数包括弹片角度、位置和长度对翼型气动性能的影响。结果表明：在失速攻角之前，弹片产生负面影响，而失速攻角之后，弹片产生预期效果，且在每个攻角下存在一个最优弹片角度，攻角越大，对应最优弹片角度也越大，但并非线性关系；失速攻角前，弹片位置越靠近尾缘，其带来的负面影响越小，而在失速攻角后，弹片越靠近前缘效果越佳，阻力系数最高降低67.04%，且失速攻角由14°推迟到16°左右；失速攻角前，弹片越短，弹片所带来负面影响越小，失速攻角之后弹片长度越长效果越好，阻力系数最大减小40%左右。

In order to improve the aerodynamic performance of the wind turbine blade airfoil,a shrapnel similar to bird feathers is attached to the upper surface of the NACA0018 airfoil and it is numerically simulated.The study of shrapnel parameters includes the effects of shrapnel angle,position and length on the aerodynamic performance of the airfoil.The results show that the shrapnel has a negative impact before the stall angle of attack,and after the stall angle of attack,the shrapnel has the expected effect.There is an optimal shrapnel angle under each angle of attack.The larger the angle of attack,the more the angle of the corresponding shrapnel is needed.But there is nonlinear relationship: before the stall angle of attack,the closer the shrapnel position is to the trailing edge,the less negative impact it has.After the stall angle of attack,the closer the shrapnel is to the leading edge,the better the drag coefficient is,which can be reduced by 67.04%.And the stall angle of attack is delayed from 14° to 16°.Before the stall angle of attack,the shorter the shrapnel,the smaller the negative impact of the shrapnel.The longer the length of the shrapnel after the stall angle of attack,the better the effect,and the drag coefficient is reduced by approximately 40%.

TK83

国家自然科学基金(51676131)；上海市科学技术委员会项目(13DZ2260900)