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Supersonic through-flow fan engine and aircraft mission performanceA study was made to evaluate potential improvement to a commercial supersonic transport by powering it with supersonic through-flow fan turbofan engines. A Mach 3.2 mission was considered. The three supersonic fan engines considered were designed to operate at bypass ratios of 0.25, 0.5, and 0.75 at supersonic cruise. For comparison a turbine bypass turbojet was included in the study. The engines were evaluated on the basis of aircraft takeoff gross weight with a payload of 250 passengers for a fixed range of 5000 N.MI. The installed specific fuel consumption of the supersonic fan engines was 7 to 8 percent lower than that of the turbine bypass engine. The aircraft powered by the supersonic fan engines had takeoff gross weights 9 to 13 percent lower than aircraft powered by turbine bypass engines.
Document ID
19900011722
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Franciscus, Leo C.
(NASA Lewis Research Center Cleveland, OH., United States)
Maldonado, Jaime J.
(Puerto Rico Univ. Mayaguez., United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1989
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.15:102304
E-4991
NASA-TM-102304
AIAA PAPER 89-2139
Meeting Information
Meeting: Aircraft Design, Systems, and Operations Conference
Location: Seattle, WA
Country: United States
Start Date: July 31, 1989
End Date: August 2, 1989
Sponsors: ASEE, AHS, AIAA
Accession Number
90N21038
Funding Number(s)
PROJECT: RTOP 505-69-61
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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