中文摘要：

为研究磨损程度对翼型绕流流场及气动性能的影响，通过CFD方法数值求解二维不可压缩雷诺平均（RANS）方程来研究风力机专用翼型S809在不同磨损深度和磨损厚度情况下的流场结构和气动性能。结果表明：前缘磨损会改变翼型设计气动外型，导致翼型的升力系数减小、阻力系数增大；当磨损厚度一定时，增加磨损深度会导致前缘分离泡和后缘流动分离的产生，但磨损深度达到一定程度后流场变化不大；当磨损深度为翼型弦长的0．5％时，磨损厚度对翼型的气动性能影响较小；当磨损深度大于翼型弦长的1．0％时，磨损厚度的影响较明显；当磨损厚度为翼型最大厚度的12％、18％及25％时，磨损深度分别超过翼型弦长的1．0％、2．0％和3．0％后翼型的气动系数变化较小，其所对应的压力系数分布曲线也基本重合。

英文摘要：

This is the result of the continuous exposure of wind turbines to the elements and of particularly high rotor blade tip speeds, which exceed a velocity of 90 m/s. These effects result in the surface of wind turbines will be worn and create rough and pock marked leading edge surfaces.In order to research on the effects of leading edge erosion on the aerodynamic characteristics of airfoil, the full two-dimensional Navier-Stokes equations and the SST k-to turbulence model were used to investigate incompressible viscous flow past the wind turbine two-dimensional airfoils with different erosion heights and thicknesses. Results showed that the leading edge erosion will change theaerodynamics shape of the airfoil and cause an increase of drag and decrease of lift for the airfoil. The erosion thickness had a little influence on the aerodynamics of the airfoil when the erosion height was less than 0.5% of the chord length, it will be serious when the erosion heights were greater than 1.0%c. The lift coefficients will have no big change when the erosion height reached a certain extent, which is 1.0%, 2.0% and 3.0% for airfoils with a 12%, 18% and 25% erosion thickness, respectively. The pressure coefficients distribution curves of the eroded airfoils overlapped each other when the erosion height reached that certain value.