基于翼型参数化方法对翼型S809进行4类不同的前缘修改，分别为前缘压力面加厚、前缘吸力面加厚、前缘上弯和前缘下弯，采用翼型设计分析软件Xfoil和商用CFD(Computational Fluid Dynamics)软件FLUENT分别对翼型气动参数和翼型周围流场进行计算。结果表明：翼型气动特性与流场特性受翼型压力面外形变化影响较小；在研究范围内，翼型吸力面加厚使得翼型在失速区升力系数增加，阻力系数减小；翼型前缘上弯使得翼型在大攻角工况下升力系数减小，阻力系数增大，且使翼型提前失速；在一定范围内翼型前缘下弯，使得翼型升力系数增大，阻力系数减小，且延迟失速。

Based on the method of airfoil parameterization,the S809 airfoil was modified,and 4 different leading edges were designed by thickening the leading edge pressure surface and leading edge suction surface,and increasing the leading edge upbending and leading edge downbending.The airfoil design and analysis software Xfoil and commercial CFD(Computational Fluid Dynamics) software FLUENT were used to calculate the aerodynamic parameters of the airfoil and the flow field around the airfoil.Results show that the deformation of pressure surface has little effect on the aerodynamic performance and flow field characteristics.Within the range of study,the lift coefficient is increased and the drag coefficient is decreased due to the thickening of the suction surface nearby the leading edge of airfoil.The upper bending leading edge of airfoil causes the lift coefficient to decrease,the drag coefficient to increase for the large angle of attack,and the airfoil stall to advance.The lower bending leading edge of airfoil leads to increased lift coefficient,decreased drag coefficient,and airfoil stall delay.

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国家自然科学基金（51676131）；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）