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title東京大学柏キャンパス極超音速風洞の気流特性について
Other TitleFlow characteristics of UT-Kashiwa hypersonic wind tunnel
Author(jpn)今村 宰; 綿貫 忠晴; 鈴木 宏二郎; 柏風洞ワーキンググループ
Author(eng)Imamura, Osamu; Watanuki, Tadaharu; Suzuki, Kojiro; Kashiwa Wind Tunnel Working Group
Author Affiliation(jpn)東京大学 大学院新領域創成科学研究科; 東京大学 大学院工学系研究科; 東京大学 大学院新領域創成科学研究科; 東京大学
Author Affiliation(eng)University of Tokyo Graduate School of Frontier Sciences; University of Tokyo School of Engineering; University of Tokyo Graduate School of Frontier Sciences; University of Tokyo
Issue Date2008-02-29
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication title第39回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2007論文集
Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007
Start page50
End page55
Publication date2008-02-29
Languagejpn
AbstractIn this study, the flow characteristics of UT (University of Tokyo)-Kashiwa hypersonic wind tunnel are obtained by measuring the Pitot pressure distribution. In this wind tunnel, the Mach 7 and 9 hypersonic nozzles are inherited from its predecessor facility in UT-Komaba Campus. From a viewpoint of the operation safety and cost, the maximum stagnation pressure at Kashiwa facility is 950 kPa, which is much lower than at Komaba facility (5 MPa). To evaluate the uniformity of the freestream of this tunnel, the Pitot pressure traverse was conducted for the Mach 7 nozzle by using the rake of 11 Pitot tubes with 20 mm intervals in the radial direction. The measurement has been done at every 30 or 45 degrees in the circumferential direction and also at some streamwise locations. The Mach number calculated from the settling chamber pressure and the test-section static pressure is nearly seven, which is almost the same as the Mach number obtained from the Pitot pressure (about 14 kPa) on the center line. The Pitot traverse shows that the uniform flow core with 120 mm diameter is formed both at the nozzle exit (200 mm in diameter) and at the center of the test section. Such ratio of the core diameter to the nozzle exit diameter seems quite reasonable, comparing to other existing hypersonic wind tunnels. The cross-sectional Mach number distribution shows slight deviation from the axi-symmetric pattern because of the misalignment of the nozzle and the test section to the tunnel center line. Consequently, the highly uniform Mach 7 flow is obtained in this facility, though the nozzle is used under the off-design operation pressure, that is, the off-design Reynolds number.
DescriptionJAXA Special Publication
宇宙航空研究開発機構特別資料
Keywordshypersonic wind tunnel; performance test; research facility; pressure distribution; Pitot tube; aerodynamic characteristic; hypersonic nozzle; stagnation pressure; stagnation temperature; Mach number; high enthalpy wind tunnel; 極超音速風洞; 性能試験; 研究施設; 圧力分布; ピトー管; 空力特性; 極超音速ノズル; よどみ点圧力; よどみ点温度; マッハ数; 高エンタルピー風洞
Document TypeConference Paper
JAXA Category特別資料
ISSN1349-113X
SHI-NOAA0063742009
Report NoJAXA-SP-07-016
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/29239


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