@inproceedings{oai:jaxa.repo.nii.ac.jp:00006592,
 author = {永井, 伸治 and 津田, 尚一 and 小山, 忠勇 and 平林, 則明 and 関根, 英夫 and 穂積, 弘一 and Nagai, Shinji and Tsuda, Shoichi and Koyama, Tadao and Hirabayashi, Noriaki and Sekine, Hideo and Hozumi, Koichi},
 book = {宇宙航空研究開発機構特別資料: 第66回　風洞研究会議論文集, JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 66th Meeting},
 month = {Mar},
 note = {The Mach 10 nozzle of the National Aerospace Laboratory phi1.27 m hypersonic wind tunnel was calibrated at lower total temperature conditions which gave reduction of thermal load of the facility and the lowest total pressure (P0 = 1.0 MPa) operation. Repeatability among multi point calibration tests and non-liquefied flow were examined by statistical uncertainty assessment of measured Mach numbers. Enlargement of the Re number range, reduction of total temperature about 100 K and heat up time of the air heater were successfully attained. Represented statistical uncertainties of flow conditions clearly show that the NAL 1.27 m tunnel has better flow uniformity than that of the AEDC VKF-C tunnel., 資料番号: AA0047428003, レポート番号: JAXA-SP-03-003},
 pages = {13--22},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {1.27m極超音速風洞の通風領域拡大:不確かさの表記と応用},
 volume = {JAXA-SP-03-003},
 year = {2004}
}