非对称钝尾缘厚度对风力机翼型气动性能的影响

Effect of Asymmetric Blunt Trailing-edge Thickness on Aerodynamic Performance of Wind Turbine Airfoils

基于参数化非对称钝尾缘翼型,研究尾缘厚度及其分配比对风力机翼型气动性能的影响规律。采用样条函数,实现翼型S834非对称钝尾缘改型型线的参数化表达。利用XFOIL软件,数值计算翼型原型和非对称钝尾缘改型的升阻力系数、升阻比以及翼型表面压力系数。结果表明:随尾缘厚度增加,升力系数一定攻角之后持续增大,改型翼型阻力系数高于原始翼型的现象更明显,升阻比先增大后减小;随下翼面尾缘厚度分配比增大,升力系数在一定攻角范围内增大,升阻比呈递增趋势;尾缘厚度及其分配比取2%弦长和13为最佳。研究结论为风力机叶片钝尾缘翼型设计和优化提供指导。

Based on parametric asymmetric blunt trailing-edge airfoil, the effects of trailing-edge thickness and its distribution ratio on aerodynamic performance of wind turbine airfoil were studied. The parametric expressions of asymmetric blunt trailing-edge modification profiles of S834 airfoil were established using the spline function. The lift and drag coefficients, lift-drag ratio, and airfoil surface pressure coefficient were calculated by XFOIL. The results show that when trailing-edge thickness increases, the lift coefficient increases after certain attack angle, and it is more obvious that the drag coefficients of modified airfoils are higher than that of original airfoil, and the lift-drag ratio increases first and then decreases. The lift coefficient in certain range of attack angle and the lift-drag ratio increase with the increasing of the trailing-edge thickness distribution ratio of the lower surface. The best trailing-edge thickness and distribution ratio are 2%c and 1：3, respectively. The research provides significant guidance for designing and optimizing blunt trailing-edge airfoil of wind turbine blade.