超声速翼身组合体激波阻力优化的EFCE算法

 超声速飞行器的横截面积分布对其激波阻力的影响十分显著,合理的机翼和机身横截面积分布可以显著降低其激波阻力。使用类别形状函数变换(CST)方法对机身进行基于横截面积分解的CST参数化外形表示,在此基础上提出了扩展的远场组元(EFCE)超声速翼身组合体激波阻力优化算法,并使用该方法对超声速客机翼身组合体进行外形优化,使其激波阻力系数降低了39%。研究结果表明:由于只进行一个方向上的面积分解,机身CST参数化所使用的参数数量和相应优化过程的计算量比机翼大幅降低;经过EFCE激波阻力优化的机身具有较为明显的面积率修形"蜂腰"特征。

Extended Far-field Composite Element Supersonic Wing-body Wave Drag Optimization Method

The wave drag of a supersonic aircraft is closely related to its cross section area distribution, and a reasonable cross section area distribution is important to wave drag reduction. This paper presents a study of the fuselage shape parameterization based on the cross section area decomposition using the class-shape-transformation (CST), and proposes an extended far-field composite element (EFCE) wing-body wave drag optimization method, as well as a supersonic wing-body shape optimization case using the EFCE method, which yields a 39% reduction of the wave drag coefficient. It is suggested that the CST parameterization and the corresponding optimization process of the fuselage shape require fewer parameters and less computation cost than the wing; and similar to the area rule shape modification, the EFCE optimization code can automatically lead to a "coke bottle" fuselage shape.