Japan Aerospace Exploration Agency
Japan Aerospace Exploration Agency
Japan Aerospace Exploration Agency
Japan Aerospace Exploration Agency
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77回風洞研究会議論文集
雑誌名(英)
JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 77th Meeting
巻
JAXA-SP-06-026
ページ
15 - 32
発行年
2007-03-28
抄録（英）
Flow-deflection angle calibration tests were conducted at JAXA 0.44 m Hypersonic Shock Tunnel with a dual-wheel model support system. Surface pressures on upper and lower surfaces of a two-dimensional wedge model were measured to identify the flow deflection angle. The flow around the model was visualized by a schlieren optical system. The tests were conducted at a nominal Mach number of 10.4. The flow-deflection angle was deducted as 0.2 degrees.
JAXA0.44m極超音速衝撃風洞と気流偏向特性試験
63333003.pdf
(2.39MB)
