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Supersonic through-flow fan engines for supersonic cruise aircraftEngine performance, weight and mission studies were carried out for supersonic through flow fan engine concepts. The mission used was a Mach 2.32 cruise mission. The advantages of supersonic through flow fan engines were evaluated in terms of mission range comparisons between the supersonic through flow fan engines and a more conventional turbofan engine. The specific fuel consumption of the supersonic through flow fan engines was 12 percent lower than the more conventional turbofan. The aircraft mission range was increased by 20 percent with the supersonic fan engines compared to the conventional turbofan.
Document ID
19780015145
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Franciscus, L. C. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1978
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-9626
NASA-TM-78889
Accession Number
78N23088
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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