基于被动流动控制理论及常用气动噪声预测方法，在S809翼型前缘吸力面附加微小翼型，以提高主翼抵抗流动分离的能力。采用数值模拟方法，在α=6°~24°来流攻角范围内计算复合翼的气动性能及噪声特性，并分析了流动控制机理。结果表明：在失速攻角之前，复合翼的气动性能表现优于原始翼型，有明显增升效果，但其气动噪声特性相比原始翼型较差；在大攻角下，前缘小翼的存在将主翼来流失速临界攻角由α=16°延缓至α=22°，且有明显降噪作用，复合翼相比原始翼型在接收点处的噪声总声压级最大可以减小7.23%。

Based on the passive control theory and the common aerodynamic noise prediction method,a small airfoil is added to the leading edge of the S809 airfoil to improve the resistance of the main airfoil to flow separation.The aerodynamic performance and noise characteristics of the compound wing are calculated for the angle of attack α=6°~24° by numerical simulation,and the flow control mechanism is analyzed.The results show that before the stall angle of attack,the aerodynamic performance of leading edge winglet to the main airfoil is better than that of the original airfoil,with significant increase in lift performance,but its aerodynamic noise performance is worse than that of the original airfoil; at large angle of attack,leading edge winglet delays the stall critical angle of attack of the main airfoil from α=16° to α=22° and has a good visibility.The composite wing can reduce 7.23% of the total sound pressure level of the airfoil at the receiving point.

TK83

国家自然科学基金（51676131）；国家自然基金国际(地区)合作与交流项目（51811530315）；上海市“科技创新行动计划”地方院校能力建设项目（19060502200）