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Parametric study of a simultaneous pitch/yaw thrust vectoring single expansion ramp nozzleIn the course of the last eleven years, the concept of thrust vectoring has emerged as a promising method of enhancing aircraft control capabilities in post-stall flight incursions during combat. In order to study the application of simultaneous pitch and yaw vectoring to single expansion ramp nozzles, a static test was conducted in the NASA-Langley 16 foot transonic tunnel. This investigation was based on internal performance data provided by force, mass flow and internal pressure measurements at nozzle pressure ratios up to 8. The internal performance characteristics of the nozzle were studied for several combinations of six different parameters: yaw vectoring angle, pitch vectoring angle, upper ramp cutout, sidewall hinge location, hinge inclination angle and sidewall containment. Results indicated a 2-to- 3-percent decrease in resultant thrust ratio with vectoring in either pitch or yaw. Losses were mostly associated with the turning of supersonic flow. Resultant thrust ratios were also decreased by sideways expansion of the jet. The effects of cutback corners in the upper ramp and lower flap on performance were small. Maximum resultant yaw vector angles, about half of the flap angle, were achieved for the configuration with the most forward hinge location.
Document ID
19890059727
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Schirmer, Alberto W.
(NASA Langley Research Center; George Washington University Hampton, VA, United States)
Capone, Francis J.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1989
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 89-2812
Accession Number
89A47098
Distribution Limits
Public
Copyright
Other

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