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Fluidic Thrust Vectoring of an Axisymmetric Exhaust Nozzle at Static ConditionsA sub-scale experimental static investigation of an axisymmetric nozzle with fluidic injection for thrust vectoring was conducted at the NASA Langley Jet Exit Test Facility. Fluidic injection was introduced through flush-mounted injection ports in the divergent section. Geometric variables included injection-port geometry and location. Test conditions included a range of nozzle pressure ratios from 2 to 10 and a range of injection total pressure ratio from no-flow to 1.5. The results indicate that fluidic injection in an axisymmetric nozzle operating at design conditions produced significant thrust-vector angles with less reduction in thrust efficiency than that of a fluidically-vectored rectangular jet. The axisymmetric geometry promoted a pressure relief mechanism around the injection slot, thereby reducing the strength of the oblique shock and the losses associated with it. Injection port geometry had minimal effect on thrust vectoring.
Document ID
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Wing, David J.
(NASA Langley Research Center Hampton, VA, United States)
Giuliano, Victor J.
(Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 1997
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
Meeting Information
Meeting: 1997 ASME Fluids Engineering Division Summer Meeting (FEDSM''97)
Country: United States
Start Date: June 22, 1997
End Date: June 26, 1997
Distribution Limits
Public Use Permitted.
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