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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 the parameterized asymmetric blunt trailing edge airfoils, the influences of the trailing edge thickness and its distribution ratio on the aerodynamic performance of wind turbine airfoils are studied. The spline function is used to realize the parametric expression of modified line of S834 asymmetrical blunt trailing edge. Using XFOIL software, the lift coefficient, lift-drag ratio and airfoil surface pressure coefficient of airfoil and asymmetric blunt trapezoid are numerically calculated. The results show that with the increase of the thickness of tail edge, the lift coefficient continues to increase after a certain angle of attack, the resistance coefficient of the modified airfoil is higher than that of the original airfoil, and the lift-drag ratio first increases and then decreases. The distribution ratio of edge thickness increases, the lift coefficient increases at a certain angle of attack, and the ratio of lift to drag shows an increasing trend. The tail thickness and its distribution ratio take 2% chord and 13 are the best. The conclusions of the study provide guidance for the design and optimization of the blunt trailing edge airfoil for wind turbine blades.