Evolutionary computation of supersonic wing shape optimization

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SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ 航空宇宙技術研究所 20000117-20000119 東京 日本

SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport National Aerospace Laboratory 20000117-20000119 Tokyo Japan

This paper discusses design optimization of wing for SuperSonic Transport (SST) using 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 in total of 66 design variables. An 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 NEC SX-4 computer using 32 PE's. The detailed analysis of the resulting Pareto front suggests a renewed interest in the arrow wing planform for the supersonic wing.

資料番号: AA0063609042

レポート番号: JAXA-SP-06-029E

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詳細情報 詳細情報について

  • CRID
    1050855511172036096
  • NII論文ID
    120006829184
  • NII書誌ID
    AA11984031
  • ISSN
    1349113X
  • Web Site
    http://id.nii.ac.jp/1696/00005767/
  • 本文言語コード
    en
  • 資料種別
    conference paper
  • データソース種別
    • IRDB
    • CiNii Articles

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