@techreport{oai:jaxa.repo.nii.ac.jp:00043776,
 author = {長洲, 秀夫 and 橋本, 登 and 穂積, 弘一 and 松崎, 貴至 and NAGASU, Hideo and HASHIMOTO, Noboru and HOZUMI, Koichi and MATSUZAKI, Takashi},
 month = {Jan},
 note = {A hypersonic wind tunnel having a 50cm diameter test section has been in operation in the National Aerospace Laboratory. In order to determine the aerodynamic characteristics of M9 nozzle, the static pressure distribution along the nozzle wall, total pressure and total tempe- rature profiles across the test section at various streamwise stations were measured. Making correction due to the real gas effect on the Mach number, the Reynolds number dependency of Mach number were determined. Condensation studies were also made and a certain degree of supersaturation was noticed. From these measurements, the flow field of the test section and the relation between stagnation condition and test section flow, which is necessary for various kinds of wind tunnel testing, were determined., 資料番号: NALTM0192000, レポート番号: NAL TM-192},
 title = {極超音速風胴M9ノズル較正試験},
 year = {1971}
}