National Aerospace Laboratory
National Aerospace Laboratory
Mitsubishi Heavy Industries Ltd.
Daiko Denshi Tsushin Ltd.
Ryoyu Keisan Co. Ltd.
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: 第70回風洞研究会議論文集
雑誌名(英)
JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 70th Meeting
巻
JAXA-SP-04-009
ページ
16 - 21
発行年
2005-02-28
抄録（英）
Development of a next-generation airplane cruising near sonic speed received considerable attention in 2002. It requires a better understanding of corresponding aerodynamic characteristics and CFD validity. As a part of the collaboration between NAL and MHI on transonic wind tunnel tests and CFD computations using NEXST-1 supersonic transport model, the effect of wall interference in NAL 2 m x 2 m transonic wind tunnel at near sonic speed condition was investigated with CFD based on Reynolds-averaged Navier-Stokes equations. The results showed considerable drag reduction (dip) at Mach number just below the drag divergence Mach number due to the interaction of wall and sting support.
小型超音速ロケット実験機の音速近傍風洞試験における壁干渉の影響
48062003.pdf
(1.49MB)
