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A preliminary assessment of the impact of 2-D exhaust-nozzle geometry on the cruise range of a hypersonic aircraft with top-mounted ramjet propulsionA theoretical study of full length and shortened, two dimensional, isentropic, exhaust nozzles integrated with top mounted ramjet propulsion nacelles were conducted. Both symmetric and asymmetric contoured nozzles with a range of angular orientations were considered. Performance comparisons to determine optimum installations for a representative hypersonic vehicle at Mach 5 cruise conditions are presented on the basis of cruise range, propulsive specific impulse, inlet area requirements, and overall lift drag ratio. The effect of approximating the nozzle internal contours with planar surfaces and the determination of viscous and frozen flow effects are also presented.
Document ID
19800023889
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Vahl, W. A. (NASA Langley Research Center Hampton, VA, United States)
Weidner, J. P. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1980
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
L-13518
NASA-TM-81841
Accession Number
80N32397
Funding Number(s)
PROJECT: RTOP 505-31-73-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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