@inproceedings{oai:jaxa.repo.nii.ac.jp:00005615,
 author = {今村, 宰 and 綿貫, 忠晴 and 鈴木, 宏二郎 and 柏風洞ワーキンググループ and Imamura, Osamu and Watanuki, Tadaharu and Suzuki, Kojiro and Kashiwa Wind Tunnel Working Group},
 book = {宇宙航空研究開発機構特別資料: 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, JAXA Special Publication: Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007},
 month = {Feb},
 note = {In 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., 資料番号: AA0063742009, レポート番号: JAXA-SP-07-016},
 pages = {50--55},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 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},
 volume = {JAXA-SP-07-016},
 year = {2008}
}