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A static investigation of yaw vectoring concepts on two-dimensional convergent-divergent nozzlesThe flow-turning capability and nozzle internal performance of yaw-vectoring nozzle geometries were tested in the NASA Langley 16-ft Transonic wind tunnel. The concept was investigated as a means of enhancing fighter jet performance. Five two-dimensional convergent-divergent nozzles were equipped for yaw-vectoring and examined. The configurations included a translating left sidewall, left and right sidewall flaps downstream of the nozzle throat, left sidewall flaps or port located upstream of the nozzle throat, and a powered rudder. Trials were also run with 20 deg of pitch thrust vectoring added. The feasibility of providing yaw-thrust vectoring was demonstrated, with the largest yaw vector angles being obtained with sidewall flaps downstream of the nozzle primary throat. It was concluded that yaw vector designs that scoop or capture internal nozzle flow provide the largest yaw-vector capability, but decrease the thrust the most.
Document ID
Document Type
Conference Paper
Berrier, B. L. (NASA Langley Research Center Hampton, VA, United States)
Mason, M. L. (NASA Langley Research Center Transonic Aerodynamics Div., Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1983
Subject Category
Report/Patent Number
AIAA PAPER 83-1288
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