@article{oai:jaxa.repo.nii.ac.jp:00031471,
 author = {田中, 英穂 and 丸田, 秀雄 and 八田, 桂三 and 網野, 一夫 and TANAKA, Hideo and MARUTA, Hideo and HATTA, Keizo and AMINO, Kazuo},
 issue = {4_B},
 journal = {東京大学宇宙航空研究所報告},
 month = {Dec},
 note = {After the completion of the air source system symbolized by the 10 m sphere reservoir, it has become very easy to get much amount of high speed air flow. Thereupon making use of this air source system, facility having two functions of high speed annular cascade wind tunnel and transonic axial flow test compressor has been constructed. This facility, only by exchanging a part of test section (inner casing, rotor, etc.), is used as the above mentioned two installations. Its specifications are as follows: 1) High speed annular cascade wind tunnel. Type: blow down type, Testsection: outer diametr 350 mm, boss ratio 0.4, Mach number: M= 1.0, Running time: about 4 min. (with M=1.0 and exit pressure of 1.0ata.). 2) Transonic axial flow test compressor. Outer diameter: 350 mm, Boss ratio: 0.7 at inlet section, Number of stage: 1, Rotational speed: 19090 rpm, Compression ratio: 1.6, Axial air velocity: 180 m/s, Relative Mach number: 1.12 at tip section of moving blade, Blade shape: double circular arc, Driving svstem: 500 KW AC motor and 400 PS air turbine., 資料番号: SA0124357000},
 pages = {451--469},
 title = {<論文>遷音速回転翼列試験機ならびに高速環状翼列風洞設備について(高速内部流体実験施設報告)},
 volume = {1},
 year = {1965}
}