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Static internal performance of a two-dimensional convergent nozzle with thrust-vectoring capability up to 60 degAn investigation was conducted at wind-off conditions in the static-test facility of the Langley 16-Foot Transonic Tunnel to determine the internal performance characteristics of a two-dimensional convergent nozzle with a thrust-vectoring capability up to 60 deg. Vectoring was accomplished by a downward rotation of a hinged upper convergent flap and a corresponding rotation of a center-pivoted lower convergent flap. The effects of geometric thrust-vector angle and upper-rotating-flap geometry on internal nozzle performance characteristics were investigated. Nozzle pressure ratio was varied from 1.0 (jet off) to approximately 5.0.
Document ID
19850010642
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Leavitt, L. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2391
L-15837
NAS 1.60:2391
Report Number: NASA-TP-2391
Report Number: L-15837
Report Number: NAS 1.60:2391
Accession Number
85N18951
Funding Number(s)
PROJECT: RTOP 505-43-90
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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