A high-lift device of a flight vehicle, the high-lift device comprising: a flap main body provided at a trailing portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in an extending direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of the tip end portion of the flap main body to an upper surface of the tip end portion of the flap main body, wherein: the vortex suppressing portion is a flow suppressing portion formed at an upper surface side of a leading edge portion of the tip end portion of the flap main body and configured to cause a flow along the upper surface of the tip end portion of the flap main body to be separated from the upper surface; and the flow suppressing portion is a projection provided along the wing span direction and projecting upward from the upper surface of the flap main body.


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    Titel :

    HIGH-LIFT DEVICE OF FLIGHT VEHICLE


    Weitere Titelangaben:

    DISPOSITIF HYPERSUSTENTATEUR DESTINE A UN AERONEF


    Beteiligte:
    ISOTANI KAZUHIDE (Autor:in) / HAYAMA KENJI (Autor:in)

    Erscheinungsdatum :

    27.09.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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