【摘要】 采用多目标遗传算法与类别形状函数变换（CST）方法相耦合的方法对翼型外形进行多目标优化设计，在攻角工作范围内，以实现高升阻比、低阻力为目标，最终得到一系列Pareto最优解集。采用指数混合函数法对优化后得到的翼型在尾缘处进行非对称加厚。通过求解二维雷诺平均纳维-斯托克斯方程（RANS）获得翼型的气动参数，结果显示：优化后的翼型与原始翼型相比具有更优的压力分布，有效提高了升力系数，减小了阻力系数。优化翼型尾缘经过加厚处理后，所有攻角下的升力系数以及升阻比系数都得到了提高，流动情况进一步改善，涡心与失速点均有一定程度的后移，表明钝尾缘翼型具有比原始翼型和优化翼型更好的升阻力特性。更多还原

【Abstract】 In this paper, the multi-objective optimization design on the airfoil plane shape is carried out by the method of coupling the multi-objective genetic algorithm and the class-shape function transform(CST) method to achieve high lift-todrag ratio with low drag in operating ranges of angle of attack, and finally obtain a series of Pareto optimal solution set. The mixed function of index method is used to increase the thickness of the trailing edge of the airfoil. The aerodynamic parameters of the airfoil are obtained by solving the 2 D Reynolds-Average Navier-Stokes(RANS) equation. The results show that the optimized airfoil has a better pressure distribution than the original airfoil, effectively increasing the lift coefficient and reducing the drag coefficient. After thickening the trailing edge of the optimized airfoil, the results show that the lift coefficient is improved at all angles of attack and the stall is delayed. Both the vortex center and the stall point are shifted back to some extent, indicating that the blunt trailing edge airfoil has better lift-to-drag characteristics than the original airfoil and the optimized airfoil.更多还原