@article{oai:jaxa.repo.nii.ac.jp:00031478,
 author = {田中, 英穂 and 丸田, 秀雄 and 網野, 一夫 and TANAKA, Hideo and MARUTA, Hideo and AMINO, Kazuo},
 issue = {3_B},
 journal = {東京大学宇宙航空研究所報告},
 month = {Sep},
 note = {V/STOL機用エンジンの開発に欠くことのできない段当り圧力比の高い遷音速圧縮機の設計資料に供するため,翼形としては二重円弧翼を使用しボス比0.7,軸流速度180 m/sec段当り圧力比1.6の遷音速試験翼列を試作し,遷音速圧縮機としての全体性能並びに圧縮機内部の流れの様子を調べ,動翼列および静翼列個々の翼列性能を明らかにした., As a component of a jet engine for V/STOL plane, a transonic axial-flow compressor with high pressure ratio per stage is hoped to be developed. At present, only a few design data for a transonic blade row are available for designers. Considering of this status quo, we made a single stage transonic axial-flow test compressor with pressure ratio of 1. 6 per stage, boss ratio of 0.7 and axial air velocity of 180 m/sec. We used double circular arc blades for both the rotating and the stationary blades. Using this test compressor, we made clear the overall performance of it and the performance of both the rotating and the stationary blade rows., 資料番号: SA0124369000},
 pages = {127--163},
 title = {<論文>遷音速軸流圧縮機の翼列性能に関する研究(V/STOL機用エンジンに関する研究)},
 volume = {1},
 year = {1965}
}