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The supersonic through-flow turbofan for high Mach propulsionA study was done to evaluate the potential improvements in aircraft turbine engine performance by incorporating unique supersonic through-flow fans. Engine performance, weight, and mission studies were carried out for conventional turbofan engines using supersonic through-flow fans. A Mach 3 commercial transport mission was considered. The advantages of the supersonic fan engines were evaluated in terms of mission range comparisons between the supersonic fan engines and conventional engines. The installed specific fuel consumption of the supersonic fan engines was 12 percent better than the conventional engines and the installed weight was projected to be 25 percent lighter. For a takeoff gross weight of 550,000 lbs, the aircraft powered by supersonic fan engines had a range capability of 6600 nm compared to 5300 nm (a 25% improvement) for conventional engines.
Document ID
19870014193
Document Type
Technical Memorandum (TM)
Authors
Franciscus, Leo C. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
July 1, 1987
Subject Category
AIRCRAFT PROPULSION AND POWER
Report/Patent Number
E-3659
NAS 1.15:100114
NASA-TM-100114
AIAA PAPER 87-2050
Funding Number(s)
PROJECT: RTOP 505-69-61
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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