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Investigation of convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft

Author:
Berrier, B. L.
Published:
Dec 1, 1980.
Physical Description:
1 electronic document
Additional Creators:
Re, R. J.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary:
An 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.
Other Subject(s):
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 19810006457.
Accession ID: 81N14972.
NASA-TP-1766.
L-13974.
Terms of Use and Reproduction:
No Copyright.
View MARC record | catkey: 15720465