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Supersonic throughflow fansSupersonic throughflow fan research, and technology needs are reviewed. The design of a supersonic throughflow fan stage, a facility inlet, and a downstream diffuser is described. The results from the analysis codes used in executing the design are shown. An engine concept intended to permit establishing supersonic throughflow within the fan on the runway and maintaining the supersonic throughflow condition within the fan throughout the flight envelope is presented.
Document ID
19890007466
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ball, C. L. (NASA Lewis Research Center Cleveland, OH, United States)
Moore, R. D. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1988
Publication Information
Publication: Von Karman Institute for Fluid Dynamics, Transonic Compressors, Volume 2
Subject Category
Aircraft Propulsion And Power
Accession Number
89N16837
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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