@inproceedings{oai:jaxa.repo.nii.ac.jp:00005764,
 author = {Matsumura, Shin and Sullivan, John P. and 真保, 雄一 and Matsumura, Shin and Sullivan, John P. and Shinbo, Yuichi},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)},
 month = {Mar},
 note = {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, preliminary SST (SuperSonic Transport) 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) which 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 the trade off the induced drag from the high aspect ratio with the wave drag from the high leading edge sweep., 資料番号: AA0063609033, レポート番号: JAXA-SP-06-029E},
 pages = {292--303},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Development of a preliminary SST planform design tool using a numerical optimization routine},
 volume = {JAXA-SP-06-029E},
 year = {2007}
}