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Performance potential of an advanced technology Mach 3 turbojet engine installed on a conceptual high-speed civil transportThe performance of an advanced technology conceptual turbojet optimized for a high-speed civil aircraft is presented. This information represents an estimate of performance of a Mach 3 Brayton (gas turbine) cycle engine optimized for minimum fuel burned at supersonic cruise. This conceptual engine had no noise or environmental constraints imposed upon it. The purpose of this data is to define an upper boundary on the propulsion performance for a conceptual commercial Mach 3 transport design. A comparison is presented demonstrating the impact of the technology proposed for this conceptual engine on the weight and other characteristics of a proposed high-speed civil transport. This comparison indicates that the advanced technology turbojet described could reduce the gross weight of a hypothetical Mach 3 high-speed civil transport design from about 714,000 pounds to about 545,000 pounds. The aircraft with the baseline engine and the aircraft with the advanced technology engine are described.
Document ID
19900000718
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Morris, Shelby J., Jr. (PRC Kentron, Inc., Hampton VA., United States)
Geiselhart, Karl A. (Planning Research Corp. Hampton, VA., United States)
Coen, Peter G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1989
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.15:4144
L-16531
NASA-TM-4144
Accession Number
90N10034
Funding Number(s)
PROJECT: RTOP 505-69-71-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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