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Static internal performance of single-expansion-ramp nozzles with thrust-vectoring capability up to 60 degAn investigation has been conducted at static conditions (wind off) in the static-test facility of the Langley 16-Foot Transonic Tunnel. The effects of geometric thrust-vector angle, sidewall containment, ramp curvature, lower-flap lip angle, and ramp length on the internal performance of nonaxisymmetric single-expansion-ramp nozzles were investigated. Geometric thrust-vector angle was varied from -20 deg. to 60 deg., and nozzle pressure ratio was varied from 1.0 (jet off) to approximately 10.0.
Document ID
19870001406
Document Type
Technical Publication (TP)
Authors
Berrier, B. L.
(NASA Langley Research Center Hampton, VA, United States)
Leavitt, L. D.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
October 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
L-15766
NAS 1.60:2364
NASA-TP-2364
Funding Number(s)
PROJECT: RTOP 505-43-90-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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