Fujitsu Ltd.
National Aerospace Laboratory
Tohoku University
Tohoku University
出版者
宇宙航空研究開発機構
出版者(英)
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料
雑誌名(英)
JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)
巻
JAXA-SP-06-029E
ページ
78 - 83
発行年
2007-03-30
会議概要(会議名, 開催地, 会期, 主催者等)
SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design 航空宇宙技術研究所 19980316-19980317 東京 日本
会議概要(会議名, 開催地, 会期, 主催者等)(英)
SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design National Aerospace Laboratory 19980316-19980317 Tokyo Japan
抄録(英)
Aerodynamic shape of a wing for NAL's SST (SuperSonic Transport) has been designed by a supersonic inverse design method. This method handles SST's wing-fuselage configurations and provides wing section's geometry at every span. The design system consists of a new inverse problem solver and a Navier-Stokes simulation. The design procedure is iterative; the baseline shape is Successively modified as the process of the inverse problem solver and Navier-Stokes simulation is iterated until the pressure distribution given by the designed wing can be regarded to converge to the target one. The design target is a NLF (Natural Laminar Flow) wing for the wing-fuselage combination at the speed of M(sub infinity) = 2.0. Several design constraints have been intended to be satisfied. By means of the method, a better wing shape which has much more desirable characteristics has been designed than that by the traditional linear theory.