一种实用的运输类飞机机翼/发动机短舱一体化优化设计方法

 发展了一套基于遗传算法优化/Navier-Stokes方程分析的运输类飞机机翼/发动机短舱一体化设计方法,提出了一系列保证该方法工程实用性的解决方案,其中包括设计变量模块化、局部优化全机分析、超临界压力分布约束条件等。通过采用适当的计算网格、并行算法及数值方法,使得基于遗传算法优化/Navier-Stakes方程分析设计方法的运算时间在工程上能够接受。运用该设计方法对下单翼运输类飞机机翼/发动机短舱一体化设计开展了单点优化和两点优化,结合二者结果对比验证了该方法的有效性和工程实用性。单点优化得到的机翼压力分布呈现无激波特点,阻力系数随马赫数变化比较剧烈;两点优化得到的机翼压力分布为弱激波形态,阻力随马赫数变化比较缓和,所设计的机翼具有更好的鲁棒性和工程实用性。

A Practical Optimization Design Method for Transport Aircraft Wing/Nacelle Integration

An aerodynamic optimization design method for wing/nacelle integration based on genetic algorithm optimization/Navier-Stokes analysis (GA/NS) is presented in this paper. A series of solutions, including the modularization of design parameters, the local optimization with full configuration analysis, and the constraints on supercritical pressure distribution, etc., are proposed to improve the engineering applicability of the aerodynamic optimization. Through the use of a verified "design grid", parallel computing and advanced numerical methods, the turnover time of genetic algorithm optimization/Navier-Stokes analysis design is made acceptable for engineering application. Single-point and dual-point optimizations for the wing/engine nacelle integration of a wing-mounted twin-jet are presented. The comparisons of the design results demonstrate the effectiveness and the engineering applicability of the method. Pressure distributions of the single-point optimization result are shock-free. Its drag coefficient increases abruptly before the desired drag divergence Mach number. Pressure distribution of the dual-point optimization result contains a weak shock. The drag coefficient varies smoothly with the Mach number. The dual-point optimization design is more robust than the single point design and more applicable in engineering.