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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    Titel :

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


    Beteiligte:
    Hutchison, R. A. (Autor:in) / Petit, J. E. (Autor:in) / Capone, F. J. (Autor:in) / Whittaker, R. W. (Autor:in)

    Kongress:

    Joint Propulsion Conference ; 1980 ; Hartford, CT


    Erscheinungsdatum :

    01.06.1980


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch







    Propulsive force vectoring

    RICE EDWARD C | Europäisches Patentamt | 2018

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