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The supersonic fan engine - An advanced concept in supersonic cruise propulsionEngine performance and mission studies were conducted for a novel turbofan engine concept incorporating a supersonic through-flow fan, and comparisons were made with two supersonic transport (SST) engine concepts of equivalent thrust and technological sophistication. It was found that in the case of an SST with a cruise speed of Mach 2.32, the through-flow fan engine may yield ranges 10 to 20% greater than the two alternatives considered. The engine has a conventional core, with the supersonic fan being driven by a concentric low-pressure turbine that is uncoupled with the single, high pressure turbine/compressor core spool. Among the topics discussed are the methods of analysis employed and perturbation studies concerning supersonic fan adiabatic efficiency, fan discharge characteristics and propulsion system weight.
Document ID
19810056569
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Franciscus, L. C.
(NASA Lewis Research Center Mission Analysis Office, Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
July 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 81-1599
Meeting Information
Meeting: Joint Propulsion Conference
Location: Colorado Springs, CO
Country: US
Start Date: July 27, 1981
End Date: July 29, 1981
Sponsors: SAE, ASME, AIAA
Accession Number
81A40973
Distribution Limits
Public
Copyright
Other

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