The 'Vortex Flap' is a novel concept aimed at reducing the lift-dependent drag due to leading-edge flow separation on highly swept, slender wings at high angles of attack. The suction effect of coiled vortices generated via controlled separation over leading-edge flap surfaces is utilized to produce an aerodynamic thrust component. This principle was verified through wind-tunnel experiments on 74-deg and 60-deg delta wings and a supersonic-cruise slender wing aircraft configuration. Adaptation of the vortex-flap for augmentation of roll-control on the 74-deg delta at high angles of attack also was demonstrated. Selected results are presented in this paper to indicate the potential of the vortex flap concept to enhance the low-speed performance, stability and control of slender wing aircraft.


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    Titel :

    Leading-edge 'Vortex Flaps' for enhanced subsonic aerodynamics of slender wings


    Beteiligte:
    Rao, D. M. (Autor:in)

    Kongress:

    International Council of the Aeronautical Sciences, Congress ; 1980 ; Munich, Germany


    Erscheinungsdatum :

    01.01.1980


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :