Multiobjective evolutionary computation for supersonic wing-shape optimization

被引：64

作者：

Obayashi, S ^{[1
]}

Sasaki, D

Takeguchi, Y

Hirose, N

机构：

[1] Tohoku Univ, Dept Aeronaut & Space Engn, Sendai, Miyagi 9808579, Japan

[2] Natl Aerosp Lab, Computat Sci Div, Tokyo 1828522, Japan

来源：

IEEE TRANSACTIONS ON EVOLUTIONARY COMPUTATION | 2000年 / 4卷 / 02期

关键词：

aerodynamics; aircraft; genetic algorithms; optimization methods;

D O I：

10.1109/4235.850658

中图分类号：

TP18 [人工智能理论];

学科分类号：

081104 ; 0812 ; 0835 ; 1405 ;

摘要：

This paper discusses the design optimization of a wing for supersonic transport (SST) using a multiple-objective genetic algorithm (MOGA), Three objective functions are used to minimize the drag for supersonic cruise, the drag for transonic cruise, and the bending moment at the wing root for supersonic cruise. The wing shape is defined by 66 design variables, A Euler flow code is used to evaluate supersonic performance, and a potential flow code is used to evaluate transonic performance, To reduce the total computational time, flow calculations are parallelized on an NEC SX-4 computer using 32 processing elements. The detailed analysis of the resulting Pareto front suggests a renewed interest in the arrow wing planform for the supersonic wing.

引用

页码：182 / 187

页数：6

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