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.


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    Title :

    Investigation of advanced thrust vectoring exhaust systems for high speed propulsive lift


    Contributors:

    Conference:

    Joint Propulsion Conference ; 1980 ; Hartford, CT


    Publication date :

    1980-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English








    Propulsive force vectoring

    RICE EDWARD C | European Patent Office | 2018

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