为得到高气动性能、低噪声的风力机专用翼型，基于参数化建模翼型，研究前缘外形对风力机翼型气动性能及气动噪声的影响规律。通过分离涡模拟方法和声学类比方程建立噪声预测方法。针对非对称翼型S809通过样条函数参数化处理前缘改形进行气动噪声计算。结果表明：翼型压力面前缘加厚，对翼型升阻力系数无明显影响，但大攻角时翼型周围压力分布均匀，流动相对稳定，且气动噪声声压级低于原始翼型，随压力面厚度增加气动噪声越大；吸力面加厚使得翼型升力系数增大，阻力系数减小，能抑制翼型失速时尾缘涡与前缘涡的生成，变形量越大气动噪声越小；翼型前缘上弯，翼型在失速区升力系数减小，阻力系数增大，流动越加不稳定，声压级随着攻角的增加呈递增趋势；翼型前缘下弯，翼型处于失速区升力系数增大，阻力系数减小，能抑制流动分离，未生成前缘涡和尾缘涡，当前缘下弯不变时，随加厚厚度增加翼型声压级呈减小趋势，且前缘下弯翼型声压级小于前缘上弯。

In order to obtain the special airfoil of wind turbine with high aerodynamic performance and low noise level,the influence of leading edge shape on aerodynamic performance and aerodynamic noise of wind airfoil is studied based on the parametric asymmetric airfoil. The method of noise prediction is established by separating vortex simulation method and acoustic analogy equation. In this paper,the aerodynamic noise of the asymmetric airfoil S809 is calculated by using Spline function parameterization to process the leading edge modification. The results show that with thickened leading edge of the airfoil pressure surface,there is no evident effect on the airfoil lift resistance coefficient,but with the large angle of attack,the pressure distribution around the airfoil is uniform,the flow is relatively stable,and the sound pressure level of the aerodynamic noise is lower than that of the original airfoil. Increasing the pressure surface thickness leads to higher aerodynamic noise. The upper bend of airfoil leading edge decreases the lift coefficient of airfoil in the stall area,increases the drag coefficient,and results in more unstable flow,and the sound pressure level increases with the increase of attack angle. When the wingshaped leading edge is bent,it increases the lift coefficient of the airfoil in the stall area,decreases the resistance coefficient,and can restrain the flow separation and inhibit the generation of the leading edge vortex trailing edge vortex.In this case,further increasing the thickening thickness leads to a decreasing trend in the airfoil sound pressure level,and the sound pressure level for the airfoil with the lower bended leading edge is less than that for the airfoil with the upper bended leading edge.

TK83

国家自然科学基金(51676131,51176129)；上海市科学技术委员会项目资助(13DZ2260900)