@article{oai:jaxa.repo.nii.ac.jp:00031480,
 author = {滝沢, 正明 and 高田, 浩之 and 八田, 桂三 and TAKIZAWA, Masaaki and TAKATA, Hiroyuki and HATTA, Keizo},
 issue = {3_B},
 journal = {東京大学宇宙航空研究所報告},
 month = {Sep},
 note = {旋回失速における翼列間などの干渉の影響を調べたり,失速パターンの構造の詳細を測定して理論解析の基礎的資料を提供したりする目的で特殊な構造を有する軸流圧縮機を設計,製作した.すなわち空気流路は完全に軸対称に作られ,ストラットその他流れに拘束を与えるものは一切なく,かつ翼列上・下流にはかなりの長さの平行流れの部分を有している.ロータ・ディスクは全部で4個あるがすべて独立に駆動される.このうちの2個に翼列をとりつけ,反転輪流圧縮機として運転した結果適当な条件のもとでは失速パターンを安定に静止させることができ,流れの場全域にわたって速度や圧力の分布を測定することができた.また翼列直前と直後の速度や圧力などがわかったので,これから翼列の非定常流中における動的な性能を推定することができ,剥離をともなう境界層のきょ動の時間遅れの大きさを知る手がかりを得た., To investigate the effects of blade row interference on the aspects of rotating stall and also to measure the detailed structures of the flow fields of rotating stall to contribute to the theoretical analysis, an axial compressor with special construction was built: The compressor has perfectly axisymmetrical flow passage without any obstacles such as struts. It also has enough length of parallel flow both upstream and downstream of the blade rows. Rotor discs, four in all, are to be driven independently to each other. Experiments were carried out with two counter-rotating blade rows attached to this compressor. Under certain operating conditions the flow pattern of rotating stall was brought to rest, and detailed measurements of the flow such as distributions of velocities and static pressures were performed through the whole flow fields. Thus flow conditions just upstream and downstream of each blade row being known, the dynamic performances of the blade row in unsteady flow were estimated, and a clue to the magnitude of the boundary layer time delay was acquired., 資料番号: SA0124371000},
 pages = {209--239},
 title = {<論文>旋回失速と翼列動特性に関する研究(V/STOL機用エンジンに関する研究)},
 volume = {1},
 year = {1965}
}