Experimental Investigation of Two-Dimensional Cascade Performance of Thin and Low-Cambered Double-Circular-Arc Blade Sections at Transonic Inlet Mach Number Range
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Former Aeroengine Division, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-300
巻
300
ページ
113
発行年
1972-10
抄録（英）
The cascade performance of double-circular-arc blades with camber angles of 3deg, 6deg, and 10deg at operating conditions typical of compressor tip sections has been investigated at inlet Mach numbers form 0.6 to 1.1 in a small transonic cascade tunnel. The cascade of the blades were tested over an appreciable range of incidence angle range(up to positive stall angle) for various combinations of stagger angles of 50deg, 55deg, 60deg and pitch-chord ratios of 1.0, 0.8, and 0.6. Test Reynolds number range was 3～7×10(exp 5), based on blade chord. Experiments were made with boundary layer suction from porous side walls at the test section to establish two-dimensional flow in the cascade.Total-pressure and flow-angle measurements were made by traversing a five-hole probe in the outlet flow from the cascade. The effect of inlet Mach numbers on mean total-pressure recoveries, mean total-pressure loss coefficients, and mean turning angles was investigated. Over the range of inlet Mach numbers experimented, the mean total-pressure loss coefficient were low, and mean turning angles did not change greatly around the design incidence angles. The variation of total-pressure loss coefficient and turning angle with incidence angle was also small and continuous throught the experimental range of incidence angle.
そり角の小さい遷音速二重円弧二次元翼列実験
naltr00300.pdf
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