A closely-coupled canard fighter with vectorable two-dimensional nozzle was designed for enhanced transonic maneuvering. The HiMAT maneuver goal of a sustained 8g turn at a free-stream Mach number of 0.9 and 30,000 feet was the primary design consideration. The aerodynamic design process was initiated with a linear theory optimization minimizing the zero percent suction drag including jet effects and refined with three-dimensional nonlinear potential flow techniques. Allowances were made for mutual interference and viscous effects. The design process to arrive at the resultant configuration is described, and the design of a powered 2-D nozzle model to be tested in the LRC 16-foot Propulsion Wind Tunnel is shown.


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    Titel :

    Canard configured aircraft with 2-D nozzle


    Beteiligte:
    Child, R. D. (Autor:in) / Henderson, W. P. (Autor:in)

    Kongress:

    Aircraft Systems and Technology Conference ; 1978 ; Los Angeles, CA


    Erscheinungsdatum :

    1978-08-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Canard configured aircraft with 2-D nozzle

    CHILD, R. / HENDERSON, W. | AIAA | 1978


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