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)