@inproceedings{oai:jaxa.repo.nii.ac.jp:00005814,
 author = {山崎, 喬 and 中北, 和之 and 中川, 宗敬 and 渡利, 實 and Yamazaki, Takashi and Nakakita, Kazuyuki and Nakagawa, Muneyoshi and Watari, Minoru},
 book = {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, JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 77th Meeting},
 month = {Mar},
 note = {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., 資料番号: AA0063333003, レポート番号: JAXA-SP-06-026},
 pages = {15--32},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {JAXA0.44m極超音速衝撃風洞と気流偏向特性試験},
 volume = {JAXA-SP-06-026},
 year = {2007}
}