远场组元(Far-field Composite Element,FCE)激波阻力优化方法是基于类别形状函数变换(Class Shape Transformation,CST)参数化方法发展出的一种超声速飞行器气动外形优化方法.文章使用CST参数化方法对超声速客机的大后掠机翼进行外形参数化,并以机翼容积和局部相对厚度为约束条件,使用FCE方法对其厚度分布进行以激波阻力最小为设计目标的快速优化.与原机翼相比,FCE优化方法使机翼激波阻力系数降低达61％,是超声速飞行器概念设计阶段降低激波阻力十分有用的优化方法.%Developed from the class shape transformation (CST) geometric parameterization method, the FCE wave drag optimization method is a new aerodynamic shape optimization method for supersonic aircraft. We use the CST parameterization method to perform the shape parameterization of a typical and large swept wing model of a supersonic aircraft. Sections 1 and 2 of the full paper explain our exploration, whose core consists of; (1) under the constraints of the total volume and local thicknesses of the swept wing, we carry out the quick optimization of the wing thickness distribution, aiming to achieve minimum wave drag; (2 ) we use the supersonic area rule to calculate the wave drag and to optimize the shape parameters of the swept wing with the Lagrange multiplier method, thus requiring no iteration and reducing computation complexity. The optimization results, given in Table 1 and Figs. 4, 5 and 6, and their analysis show preliminarily that, compared with the baseline wing model, our optimization method can reduce the wave drag coefficient by 61% , thus being a useful method for aerodynamic shape optimization so as to reduce the wave drag at the stage of the conceptual design of a supersonic aircraft.
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