Development of a preliminary SST planform design tool using a numerical optimization routine

Material type: 文書・図像類

Author: 松村, 晋ほか

Publisher: 航空宇宙技術研究所

Publication date: 2000-12

Material Format: Digital

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Note (General)：: 航空宇宙技術研究所 17-19 Jan. 2000 東京日本National Aerospace Laboratory 17-19 Jan. 2000 Tokyo Japan数値最適化に単純降下法を用い、空力解析に揚力面理論を用いて、SST翼の平面形基本設計用のプログラムを開発した。翼平面形を一定...

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Material Type: 文書・図像類
Title: Development of a preliminary SST planform design tool using a numerical optimization routine
Author/Editor: 松村, 晋
Sullivan, John P.
真保, 雄一
Matsumura, Shin
Shinbo, Yuichi
Author Heading: 松村, 晋
Sullivan, John P.
真保, 雄一
Matsumura, Shin
Shinbo, Yuichi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 2000-12
Publication Date (W3CDTF): 2000-12
Alternative Title: 数値最適化手順を用いたSST平面形状基本設計ツールの開発
Periodical title: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory
No. or year of volume/issue: 49T
Volume: 49T
Pages: 97-108
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: eng
Subject Heading: 数値最適化
基本設計ツール
SST
超音速輸送機
単純降下法
矢羽根翼
非粘性抵抗
誘導抵抗
造波抵抗
numerical optimization
preliminary design tool
supersonic transport
simplex downhill method
arrow wing
inviscid drag
induced drag
wave drag
Target Audience: 一般
Note (General): 航空宇宙技術研究所 17-19 Jan. 2000 東京日本
National Aerospace Laboratory 17-19 Jan. 2000 Tokyo Japan
数値最適化に単純降下法を用い、空力解析に揚力面理論を用いて、SST翼の平面形基本設計用のプログラムを開発した。翼平面形を一定の平面面積の矢羽根翼に限定し、その幾何形状を多くとも7つの独立な設計変数で表現した。最適化のための目的関数は、幾何形状の制約を侵した場合のペナルティー関数を付加した設計条件(M=2、C(sub L)=0.1)での非粘性抵抗であった。このプログラムは空力的な解析のみを行うためのものであるので、非現実的な平面形を避けるため、構造や製造など複合的に考察した制約に基づき、変数は限定されているか一定であった。その結果、設計変数は、最適化の鍵となる役割果たす主変数(アスペクト比、細長比、内側の前縁の後退角)の組と、幾何的制約を満たすために用いられる2次変数の組に分けられるであろう。最後に、多点設計への準備として、飛行高度と飛行機重量を同時に保ちながら、いくつかの設計マッハ数とそれに対応する設計揚力係数について最適化を行った。その結果、得られた最適幾何形状は、高アスペクト比に起因する誘導抵抗と前縁の大きな後退による造波抵抗とのかね合いで変化した。
A preliminary SST wing planform design program was developed using the simplex downhill method for numerical optimization and lifting surface theory for aerodynamic analysis. The wing planform was restricted to an arrow wing with a constant planform area, and the geometry was represented by at most seven independent design variables. The objective function of the optimization was the inviscid drag at design condition (M = 2, C(sub L) = 0.1) with penalty functions for the violation of geometry constraints. Because the program only performs aerodynamic analysis, variables were bound or held constant based on multidisciplinary considerations such as structural and manufacturing restrictions, in order to avoid unrealistic planforms. The results showed the design variables could be grouped into a set of primary variables (aspect ratio, slenderness ratio, sweep angle of inner leading edge) that played key roles to the optimization, and a set of secondary variables, primarily used to satisfy the geometry constraints. Finally, as a preparation for the multi-point design, the optimization was performed at several design-Mach numbers and corresponding design-lift coefficients while keeping the flight altitude and the weight of the aircraft the same. The resulting optimum geometry changed to trade off the induced drag from the high aspect ratio with the wave drag from the high leading edge sweep.
資料番号: AA0028638013
レポート番号: NAL SP-49T
Access Restrictions: 限定公開
Periodical Title (NCID): AN10097345
https://ci.nii.ac.jp/ncid/AN10097345
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ