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针对混合层流流动控制(HLFC)机翼气动优化设计问题,采取将自由变形(FFD)参数化方法、基于紧支函数的径向基函数(RBF)动网格技术和改进的微分进化算法直接与CFD数值评估方法进行耦合的方式,建立了可同时考虑吸气控制分布和机翼型面影响的HLFC机翼气动优化设计系统.其中转捩预测方法为eN.针对无限展长后掠翼,利用该系统进行了单点、考虑升力系数变化的多点以及同时考虑了升力系数和马赫数变化的多点鲁棒优化设计研究.设计结果表明:HLFC机翼的有利压力分布形态为头部峰值较低,峰值之后为一定的逆压力梯度,之后为大小适宜的顺压力梯度.相比于初始构型,单点优化设计结果凭借有利压力分布形态将转捩点从弦长的2％推迟到了弦长的57％,但是吸气控制强度却只有初始构型的一半左右.多点设计结果表明:提高吸气控制强度尤其是吸气区域首尾2部分的吸气强度,有利于提高HLFC机翼的鲁棒性.当马赫数在0.77～0.79的范围内变化,升力系数在0.53～0.65的范围内变化时,多点设计结果都能维持37％弦长以上的层流区.“,”Regarding the issue about Hybrid Laminar Flow Control (HLFC) wings aerodynamic design,we establish an aerodynamic optimization design system by directly coupling the CFD method with the optimization technologies including the Free Form Deformation (FFD) parameterization,the Radial Basis Function (RBF) dynamic mesh method based on compact support radial basis function,and the improved differential evolution.The transition prediction model is eN method.For the infinite span swept wing,the system proposed is used to do single-point design,and multi-point robust designs which consider the variation of lift coefficients and Mach numbers.Optimization results show that the best pressure distribution of HLFC wings has a low negative pressure peak at the leading edge,followed by a gently adverse pressure gradient.Then,just behind the adverse pressure gradient,there exists a suitable favorable pressure gradient.Compared with the original model,the transition location of the single-point design result,which has a good pressure distribution,is delayed from 2％ of the chord to the chord length of 57％,but the suction control strength is only half of that of the original model.Multi-point design results indicate that increasing the strength of suction control,especially at the beginning and end of the suction control region,is conducive to improving the robustness of HLFC wings.When the Mach number is in the range of 0.77-0.79 and the lift coefficient is in the range of 0.53-0.65,the multi-point design results can maintain laminar flow region over the chord length of 37％.