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Overall and blade element performance of a 1.20-pressure-ratio fan stage with rotor blades reset -5 ̊

George W. Lewis (Jr.)Walter Martin OsbornRoyce D. Moore

出版	U.S. National Aeronautics and Space Administration, 1976
URL	http://books.google.com.hk/books?id=qj2y0FdG7s4C&hl=&source=gbs_api

註釋A 51-cm-diam model of a fan stage for a short haul aircraft was tested in a single stage-compressor research facility. The rotor blades were set 5 deg toward the axial direction (opened) from design setting angle. Surveys of the air flow conditions ahead of the rotor, between the rotor and stator, and behind the stator were made over the stable operating range of the stage. At the design speed of 213.3 m/sec and a weight flow of 31.5 kg/sec, the stage pressure ratio and efficiency were 1.195 and 0.88, respectively. The design speed rotor peak efficiency of 0.91 occurred at the same flow rate.