为了获得机翼最优的气动外形，提出了一种多偏转参数与非均匀B样条结合的翼型前后缘连续偏转变形方法。以NACA3412翼型为研究实例，对翼型曲线进行参数化重构。以翼型前、后缘偏转位置和偏转角度为变化参数，模拟分析了不同变形状态对翼型气动特性的影响规律。以翼型升力系数和升阻比为优化目标，以前、后缘的偏转角度、偏转位置以及过渡段长度等六个偏转参数为设计变量，采用多目标遗传算法和ANSYS软件进行优化设计。结果表明，与基础翼型相比，优化后的变弯度翼型的升阻比提升约19.26%，升力提升约44.43%，明显改善了翼型的气动性能。

Aiming at the optimal aerodynamic shape of the airfoil, a continuous deflection deformation law for the leading and trailing edge of an airfoil combining multiple-parameter deflection and B-spline was proposed. Taking NACA3412 airfoil as an example, the parametric reconstruction of airfoil curve was carried out. Numerical simulations were adopted to analysis the influence of the deflection position and angle of leading edge and trailing edge on the aerodynamic performance of the airfoil. Take the airfoil lift-to-drag ratio and lift coefficient as the optimization targets, and with six deflection parameters, including leading edge deflection angle, leading edge deflection position, leading edge transition section length, trailing edge deflection angle, trailing edge deflection position and trailing edge transition section length as the design variables, the multi-objective genetic algorithm NSGA-Ⅱ, and ANSYS software were used to optimize the variable-camber airfoil. Compared with the basic airfoil, the lift-drag ratio of the optimized variable-camber airfoil was increased by more than 19.26% while the lift coefficient was increased by more than 44.43%.