Tohoku University Graduate School
Tohoku University Faculty of Engineering
Tohoku University Faculty of Engineering
Fujitsu Ltd Supercomputer Systems Engineering Division
National Aerospace Laboratory Applied Mathematics Laboratory, Computational Science Division
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
巻
37
ページ
87 - 92
発行年
1998-02
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 12-13 Jun. 1997 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 12-13 Jun. 1997 Tokyo Japan
The inverse design method for Supersonic Transport (SST) is developed. This method utilizes Takanishi's residual-correction concept, which is used in the transonic inverse problem. The difference between the computed pressure distribution of given wing and the prescribed target pressure distribution is iteratively reduced by solving the integrodifferential form of Linearized Small Perturbation (LSP) equation. The pressure distribution is computed by Euler/Navier-Stokes equation. The numerical results show the possibility of using this method to the design of SST.
Inverse design method for wing of supersonic transport
nalsp0037014.pdf
(349.88KB)
