摘要:基于 NREL S809翼型,研究尾翼摆角对于翼型气动性能的影响。通过对比升阻力系数的模拟值与实验值,排除了网格质量对翼型气动性能的影响,验证了利用 S-A(Spalart-Allmaras)湍流模型对风力机翼型进行计算的有效性,确定了合理的模拟方案,分析了翼型的气动性能。在此基础上,将 S809翼型进行了尾缘变形,生成 S809上摆-5°、下摆5°、10°及15°这4种变形翼型。再利用CFD (computational fluid dynamics)软件对它们进行数值计算,分析了各个翼型升阻力系数及流场特性。研究表明,随着尾缘下摆角度的增加,变形翼型上下表面压差逐渐增大,下摆翼型在升阻力特性方面有较大改善。但随着翼型下摆角度的增大,翼型产生分离涡的攻角却随之减小,更易失速。而上摆翼型升阻力特性及失速特性均不如原始翼型。%NREL S809 airfoil was selected as an object to study the impact of trailing edge angle on its aerodynamic performances.The simulation results were compared with the experiment ones to rule out the grid quality effects on aerodynamic performance,the effectiveness of S-A (Spalart-Allmaras)turbulence model was verified and a reasonable simulation scheme was made sure to analyze the airfoil well and truly.On this basis,the S809 trailing edge swing angle was altered to generate S809 -5°,5°,10°,15°deformed airfoils.Then the CFD software was used to analyze numerically each airfoil’s aerodynamic characteristics.With the increase of trailing edge swing angle,the differential pressure on the upper and lower surfaces of the airfoil becomes bigger.So for the positive swing angle airfoils the lift and resistance characteristics are improved,however,when the airfoil swing angle is increased,the angle of attack becomes smaller and the separation vortex would appear.For negative swing angle airfoils,all of the lift,resistance and stalling characteristics are worse.