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Supersonic through-flow fan designThe NASA Lewis Research Center has embarked on a program to experimentally prove the concept of a supersonic through-flow fan which is to maintain supersonic velocities throughout the compression system with only weak shock-wave flow losses. The detailed design of a supersonic through-flow fan and estimated off-design performance with the use of advanced computational codes are described. A multistage compressor facility is being modified for the newly designed supersonic through-flow fan and the major aspects of this modification are briefly described.
Document ID
19870013248
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Schmidt, James F. (NASA Lewis Research Center Cleveland, OH, United States)
Moore, Royce D. (NASA Lewis Research Center Cleveland, OH, United States)
Wood, Jerry R. (NASA Lewis Research Center Cleveland, OH, United States)
Steinke, Ronald J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1987
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 87-1746
NAS 1.15:88908
NASA-TM-88908
E-3492
Report Number: AIAA PAPER 87-1746
Report Number: NAS 1.15:88908
Report Number: NASA-TM-88908
Report Number: E-3492
Accession Number
87N22681
Funding Number(s)
PROJECT: RTOP 505-62-61
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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