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.
Aerodynamic wing design for NAL's SST using iterative inverse approach
63609012.pdf
(2.65MB)
