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Performance of a straight stator and a tilted stator tested with a high-solidity high-pressure-ratio transonic rotorOverall stage and stator blade element performance with straight stator and tilted stator in transonic axial flow compressor stage
Document ID
19650003088
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Cullom, R. R. (NASA Lewis Research Center Cleveland, OH, United States)
Goldstein, A. W. (NASA Lewis Research Center Cleveland, OH, United States)
Schacht, R. L. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
October 1, 1959
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-99
Accession Number
65N12689
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
STATOR BLADE
TRANSONIC FLOW
AXIAL FLOW COMPRESSOR

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