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Static internal performance of an axisymmetric nozzle with multiaxis thrust-vectoring capabilityAn investigation was conducted in the static test facility of the Langley 16 Foot Transonic Tunnel in order to determine the internal performance characteristics of a multiaxis thrust vectoring axisymmetric nozzle. Thrust vectoring for this nozzle was achieved by deflection of only the divergent section of this nozzle. The effects of nozzle power setting and divergent flap length were studied at nozzle deflection angles of 0 to 30 at nozzle pressure ratios up to 8.0.
Document ID
19910005812
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Carson, George T., Jr. (NASA Langley Research Center Hampton, VA, United States)
Capone, Francis J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
L-16809
NAS 1.15:4237
NASA-TM-4237
Report Number: L-16809
Report Number: NAS 1.15:4237
Report Number: NASA-TM-4237
Accession Number
91N15125
Funding Number(s)
PROJECT: RTOP 505-62-71-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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