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Effects of sidewall geometry on the installed performance of nonaxisymmetric convergent-divergent exhaust nozzlesThe investigation was conducted at static conditions and over a Mach number range from 0.6 to 1.2. Angle of attack was held constant at 0 deg. High pressure air was used to simulate jet exhaust flow at ratios of jet total pressure to free-stream static pressure from 1 (jet off) to approximately 10. Sidewall cutback appears to be a viable way of reducing nozzle weight and cooling requirements without compromising installed performance.
Document ID
19810007461
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Yetter, J. A.
(George Washington Univ. Hampton, Va., United States)
Leavitt, L. D.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1771
L-13826
Accession Number
81N15976
Funding Number(s)
PROJECT: RTOP 530-03-13-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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