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Investigation of advanced thrust vectoring exhaust systems for high speed propulsive liftThe paper presents the results of a wind tunnel investigation conducted at the NASA-Langley research center to determine thrust vectoring/induced lift characteristics of advanced exhaust nozzle concepts installed on a supersonic tactical airplane model. Specific test objectives include: (1) basic aerodynamics of a wing body configuration, (2) investigation of induced lift effects, (3) evaluation of static and forward speed performance, and (4) the effectiveness of a canard surface to trim thrust vectoring/induced lift forces and moments.
Document ID
19800057020
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hutchison, R. A.
(NASA Langley Research Center Hampton, VA, United States)
Petit, J. E.
(Boeing Military Airplane Co. Seattle, Wash., United States)
Capone, F. J.
(NASA Langley Research Center High Speed Aerodynamics Div., Hampton, Va., United States)
Whittaker, R. W.
(General Electric Co. Evendale, Ohio, United States)
Date Acquired
August 10, 2013
Publication Date
June 1, 1980
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 80-1159
Meeting Information
Meeting: Joint Propulsion Conference
Location: Hartford, CT
Start Date: June 30, 1980
End Date: July 2, 1980
Sponsors: AIAA, SAE, and ASME,
Accession Number
80A41190
Distribution Limits
Public
Copyright
Other

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