The 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.
Investigation of advanced thrust vectoring exhaust systems for high speed propulsive lift
Joint Propulsion Conference ; 1980 ; Hartford, CT
1980-06-01
Conference paper
No indication
English
Advanced Technology Thrust Vectoring Exhaust Systems
AIAA | 1974
|Advanced technology thrust vectoring exhaust systems
AIAA | 1973
|