Multiobjective GA for SST wing-body shape design

Daisuke Sasaki; Guowei Yang; Shigeru Obayashi

doi:10.1016/B978-044450680-1/50065-6

Multiobjective GA for SST wing-body shape design

Daisuke Sasaki, Guowei Yang, Shigeru Obayashi

Creative Flow Research Division

Research output: Chapter in Book/Report/Conference proceeding › Chapter

Abstract

In this research, multiobjective optimization system has been developed to reduce the aerodynamic drag and the sonic boom for SST wing-body configuration. Wing and fuselage are defined by 131 design variables and optimized at the same time. Multiblock grids around SST wing-body configuration are generated automatically and an Euler solver is used to evaluate the aerodynamic performance of SST wing-body configuration. Sonic boom is evaluated based on the equivalent area distribution by Darden. MOGA is used as an optimizer of the present optimization. To reduce the large computation time, CFD computations are parallelized by a simple master-slave concept on SGI ORIGIN 2000 at The Institute of Fluid Science at Tohoku University.

Original language	English
Title of host publication	Parallel Computational Fluid Dynamics 2002
Subtitle of host publication	New Frontiers and Multi-Disciplinary Applications
Publisher	Elsevier Inc.
Pages	515-522
Number of pages	8
ISBN (Electronic)	9780080538426
ISBN (Print)	9780444506801
DOIs	https://doi.org/10.1016/B978-044450680-1/50065-6
Publication status	Published - 2003 Apr 25

Keywords

Optimization Problems

ASJC Scopus subject areas

Mathematics(all)

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10.1016/B978-044450680-1/50065-6

Cite this

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title = "Multiobjective GA for SST wing-body shape design",

abstract = "In this research, multiobjective optimization system has been developed to reduce the aerodynamic drag and the sonic boom for SST wing-body configuration. Wing and fuselage are defined by 131 design variables and optimized at the same time. Multiblock grids around SST wing-body configuration are generated automatically and an Euler solver is used to evaluate the aerodynamic performance of SST wing-body configuration. Sonic boom is evaluated based on the equivalent area distribution by Darden. MOGA is used as an optimizer of the present optimization. To reduce the large computation time, CFD computations are parallelized by a simple master-slave concept on SGI ORIGIN 2000 at The Institute of Fluid Science at Tohoku University.",

keywords = "Optimization Problems",

author = "Daisuke Sasaki and Guowei Yang and Shigeru Obayashi",

note = "Funding Information: The present computation was carried out in parallel using ORIGIN2000 in the Institute of Fluid Science, Tohoku University. The third author{\textquoteright}s research has been partly supported by Bombardier Aerospace, Toronto, Canada. The authors would like to thank Dr. Yoshida and NAL{\textquoteright}s SST Design Team for providing many useful data. Publisher Copyright: {\textcopyright} 2003 Elsevier B.V. All rights reserved.",

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doi = "10.1016/B978-044450680-1/50065-6",

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AU - Sasaki, Daisuke

AU - Yang, Guowei

AU - Obayashi, Shigeru

N1 - Funding Information: The present computation was carried out in parallel using ORIGIN2000 in the Institute of Fluid Science, Tohoku University. The third author’s research has been partly supported by Bombardier Aerospace, Toronto, Canada. The authors would like to thank Dr. Yoshida and NAL’s SST Design Team for providing many useful data. Publisher Copyright: © 2003 Elsevier B.V. All rights reserved.

PY - 2003/4/25

Y1 - 2003/4/25

N2 - In this research, multiobjective optimization system has been developed to reduce the aerodynamic drag and the sonic boom for SST wing-body configuration. Wing and fuselage are defined by 131 design variables and optimized at the same time. Multiblock grids around SST wing-body configuration are generated automatically and an Euler solver is used to evaluate the aerodynamic performance of SST wing-body configuration. Sonic boom is evaluated based on the equivalent area distribution by Darden. MOGA is used as an optimizer of the present optimization. To reduce the large computation time, CFD computations are parallelized by a simple master-slave concept on SGI ORIGIN 2000 at The Institute of Fluid Science at Tohoku University.

AB - In this research, multiobjective optimization system has been developed to reduce the aerodynamic drag and the sonic boom for SST wing-body configuration. Wing and fuselage are defined by 131 design variables and optimized at the same time. Multiblock grids around SST wing-body configuration are generated automatically and an Euler solver is used to evaluate the aerodynamic performance of SST wing-body configuration. Sonic boom is evaluated based on the equivalent area distribution by Darden. MOGA is used as an optimizer of the present optimization. To reduce the large computation time, CFD computations are parallelized by a simple master-slave concept on SGI ORIGIN 2000 at The Institute of Fluid Science at Tohoku University.

KW - Optimization Problems

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SN - 9780444506801

SP - 515

EP - 522

BT - Parallel Computational Fluid Dynamics 2002

PB - Elsevier Inc.

ER -

Multiobjective GA for SST wing-body shape design

Abstract

Keywords

ASJC Scopus subject areas

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