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Supersonic through-flow fan assessmentA study was conducted to assess the performance potential of a supersonic through-flow fan engine for supersonic cruise aircraft. It included a mean-line analysis of fans designed to operate with in-flow velocities ranging from subsonic to high supersonic speeds. The fan performance generated was used to estimate the performance of supersonic fan engines designed for four applications: a Mach 2.3 supersonic transport, a Mach 2.5 fighter, a Mach 3.5 cruise missile, and a Mach 5.0 cruise vehicle. For each application an engine was conceptualized, fan performance and engine performance calculated, weight estimates made, engine installed in a hypothetical vehicle, and mission analysis was conducted.
Document ID
19890007472
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Kepler, C. E. (United Technologies Research Center East Hartford, CT, United States)
Champagne, G. A. (United Technologies Research Center East Hartford, CT, United States)
Date Acquired
September 5, 2013
Publication Date
November 1, 1988
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
UTRC-R88-957367-31
NASA-CR-182202
NAS 1.26:182202
Report Number: UTRC-R88-957367-31
Report Number: NASA-CR-182202
Report Number: NAS 1.26:182202
Accession Number
89N16843
Funding Number(s)
CONTRACT_GRANT: NAS3-24843
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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