JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
63333003.pdf2.34 MB
titleJAXA0.44m極超音速衝撃風洞と気流偏向特性試験
Other TitleFlow-deflection angle calibration of JAXA 0.44 m Hypersonic Shock Tunnel
Author(jpn)山崎 喬; 中北 和之; 中川 宗敬; 渡利 實
Author(eng)Yamazaki, Takashi; Nakakita, Kazuyuki; Nakagawa, Muneyoshi; Watari, Minoru
Author Affiliation(jpn)宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構
Author Affiliation(eng)Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency; Japan Aerospace Exploration Agency
Issue Date2007-03-28
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication title第77回風洞研究会議論文集
Proceedings of the Wind Tunnel Technology Association 77th Meeting
Start page15
End page32
Publication date2007-03-28
Languagejpn
AbstractFlow-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.
DescriptionJAXA Special Publication
宇宙航空研究開発機構特別資料
Keywordsflow deflection; hypersonic shock tunnel; hypersonic flow; pressure sensitive paint; pressure measurement; measuring instrument; wind tunnel model; Schlieren photography; flow visualization; 気流偏向; 極超音速衝撃風洞; 極超音速流; 感圧塗料; 圧力測定; 測定装置; 風洞模型; シュリーレン写真法; 流れの可視化
Document TypeConference Paper
JAXA Category特別資料
ISSN1349-113X
SHI-NOAA0063333003
Report NoJAXA-SP-06-026
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/51944


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