@techreport{oai:jaxa.repo.nii.ac.jp:00044544,
 author = {坂口, 一 and 近藤, 博 and 高森, 晋 and 岩下, 敬吾 and SAKAGUCHI, Hajime and KOND0, Hiroshi and TAKAMORI, Susumu and IWASHITA, Keigo},
 month = {Oct},
 note = {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., 資料番号: NALTR0300000, レポート番号: NAL TR-300},
 title = {そり角の小さい遷音速二重円弧二次元翼列実験},
 year = {1972}
}