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Supersonic fan engines for military aircraftEngine performance and mission studies were performed for turbofan engines with supersonic through-flow fans. A Mach 2.4 CTOL aircraft was used in the study. Two missions were considered: a long range penetrator mission and a long range intercept mission. The supersonic fan engine is compared with an augmented mixed flow turbofan in terms of mission radius for a fixed takeoff gross weight of 75,000 lbm. The mission radius of aircraft powered by supersonic fan engines could be 15 percent longer than aircraft powered with conventional turbofan engines at moderate thrust to gross weight ratios. The climb and acceleration performance of the supersonic fan engines is better than that of the conventional turbofan engines.
Document ID
19830026676
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Franciscus, L. C. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
October 19, 1983
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-83499
NAS 1.15:83499
E-1833
Meeting Information
Meeting: Aircraft Design Systems and Operations Meeting
Location: Fort Worth, TX
Country: United States
Start Date: October 17, 1983
End Date: October 19, 1983
Sponsors: AHS, AIAA
Accession Number
83N34947
Funding Number(s)
PROJECT: RTOP 505-40-82
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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