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Performance of inlet stage of transonic compressorThe overall and blade-element performances are presented over the stable flow operating range of the stage at the design tip speed of 426 m/sec. Stage peak efficiency of 0.83 was obtained at a weight flow of 28.8 kg/sec and a pressure ratio of 1.52. The stall margin for the stage was 8 percent based on weight flow and pressure ratio at peak efficiency and stall. The rotor appears to be stalling prematurely as evidenced by high rotor tip losses.
Document ID
19760009935
Document Type
Technical Memorandum (TM)
Authors
Urasek, D. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Steinke, R. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Lewis, G. W., Jr.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1976
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-3345
E-8056
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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