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使用类别形状函数变换(CST)参数化方法对超声速翼身组合体的机身和机翼外形进行参数化表示,在充分利用机翼与机身之间气动干扰的基础上提出了基于远场组元的机翼和机身激波阻力协同优化(CoFCE)算法,并对其计算量和优化结果同机翼和机身外形交替进行优化的扩展的远场组元(EFCE)激波阻力优化方法开展对比。研究结果表明:随着参数数量的增加,CoFCE算法的计算量更大,其优化效果明显优于EFCE算法;经过CoFCE方法优化的翼身组合体超声速巡航状态下的升阻比有大幅提高。
The parametric method of CST is used to parametrize the fuselage and wing profile of the supersonic wing-body assembly. Based on the full use of the aerodynamic interference between the wing and the fuselage, Element Coefficient Optimization (CoFCE) Algorithm for Airfoil and Body Radiofrequency (HF) Coefficient and Extensions of Far Field Fragment (EFCE) Shock Resistance Optimization with Optimized Calculation Results and Optimization Results with Alternating Wing and Body Profile To contrast. The results show that as the number of parameters increases, the computational load of CoFCE algorithm is larger and its optimization effect is better than that of EFCE algorithm. The lift-drag ratio of wing-body combination supersonic cruise optimized by CoFCE method increases greatly.