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Investigation of convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraftAn investigation was conducted of isolated convergent-divergent nozzles to determine the effect of several design parameters on nozzle performance. Tests were conducted using high pressure air for propulsion simulation at Mach numbers from 0.60 to 2.86 at an angle of attack of 0 deg and at nozzle pressure ratios from jet off to 46.0. Three power settings (dry, partial afterburning, and maximum afterburning), three nozzle lengths, and nozzle expansion ratios from 1.22 to 2.24 were investigated. In addition, the effects of nozzle throat radius and a cusp in the external boattail geometry were studied. The results of this study indicate that, for nozzles operating near design conditions, increasing nozzle length increases nozzle thrust-minus-drag performance. Nozzle throat radius and an external boattail cusp had negligible effects on nozzle drag or internal performance.
Document ID
19810006457
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Berrier, B. L. (NASA Langley Research Center Hampton, VA, United States)
Re, R. J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
L-13974
NASA-TP-1766
Accession Number
81N14972
Funding Number(s)
PROJECT: RTOP 505-32-13-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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