@inproceedings{oai:jaxa.repo.nii.ac.jp:00005813,
 author = {香西, 政孝 and 上野, 真 and 塩原, 辰郎 and 小松, 行夫 and 唐澤, 敏夫 and 小池, 陽 and 須谷, 記和 and 我那覇, 義人 and 今, 直樹 and 原口, 智裕 and Kozai, Masataka and Ueno, Makoto and Shiohara, Tatsuro and Komatsu, Yukio and Karasawa, Toshio and Koike, Akira and Sudani, Norikazu and Ganaha, Yoshito and Kon, Naoki and Haraguchi, Tomohiro},
 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 = {In the JAXA 2 m x 2 m Transonic Wind Tunnel, there have been more needs of wind tunnel users for high measurement accuracy to develop aircraft and launch vehicles with high performance. To achieve higher accuracy, more elaborate calibration tests to calculate freestream flow conditions have been conducted in this wind tunnel. To obtain test section Mach numbers exactly, test section static pressures must be measured precisely. However, the measurement of test section static pressure is difficult for transonic flows, especially high subsonic flows because of probe nose effects, blockage effects, support interference, and so on. A series of calibration tests is conducted to optimize the static pressure probe for transonic flows and to determine the test section Mach number in the model location from the plenum chamber Mach number., 資料番号: AA0063333002, レポート番号: JAXA-SP-06-026},
 pages = {6--14},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {JAXA2m×2m遷音速風洞における測定部マッハ数検定試験},
 volume = {JAXA-SP-06-026},
 year = {2007}
}