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A static investigation of a simultaneous pitch and yaw thrust vectoring 2-D C-D nozzleAn investigation has been conducted in the static test facility of the Langley 16-Foot Transonic Tunnel to determine the internal performance and flow-turning capability of a two-dimensional convergent-divergent nozzle. Thrust vectoring in the pitch plane was provided by rotation of the divergent flaps. The exhaust stream was turned in the yaw direction by deflection of yaw flaps hinged at the end of the nozzle sidewalls. The yaw flap hinge location was varied along the divergent region of the nozzle at four locations including the exit plane and the throat plane. The three hinge locations upstream of the nozzle exit plane required the downstream corners of both upper and lower divergent flaps to be cut off to eliminate interference when the yaw flaps were deflected. Three different lengths of yaw flaps were tested at several angles of deflection. The nozzle simulated a dry power setting with an expansion ratio typical of subsonic cruise and was tested at nozzle pressure ratios from 2.0 to 7.0.
Document ID
19880058391
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Taylor, John G.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
July 1, 1988
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 88-2998
Accession Number
88A45618
Distribution Limits
Public
Copyright
Other

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