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Comparative investigation of multiplane thrust vectoring nozzlesThe inflight aerodynamic performance of multiplane vectoring nozzles is critical to development of advanced aircraft and flight control systems utilizing thrust vectoring. To investigate vectoring nozzle performance, subscale models of two second-generation thrust vectoring nozzle concepts currently under development for advanced fighters were integrated into an axisymmetric test pod. Installed drag and vectoring performance characteristics of both concepts were experimentally determined in wind tunnel testing. CFD analyses were conducted to understand the impact of internal flow turning on thrust vectoring characteristics. Both nozzles exhibited drag comparable with current nonvectoring axisymmetric nozzles. During vectored-thrust operations, forces produced by external flow effects amounted to about 25 percent of the total force measured.
Document ID
19920066234
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Capone, F.
(NASA Langley Research Center Hampton, VA, United States)
Smereczniak, P.
(NASA Langley Research Center Hampton, VA, United States)
Spetnagel, D.
(McDonnell Aircraft Co. Saint Louis, MO, United States)
Thayer, E.
(Pratt & Whitney Group West Palm Beach, FL, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 92-3263
Accession Number
92A48858
Distribution Limits
Public
Copyright
Other

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