The present invention relates to an airfoil comprising a leading edge flap (210) providing a rigid leading edge surface profile contour (212); a central lifting section (220) aft of the rigid leading edge flap (210); a bottom side (208) comprising a lower surface contour section (232) formed at least by a lower surface section (228) of the rigid leading edge surface profile contour (212) and by a bottom surface (224) of the central lifting section (220); and a top side (206) comprising an upper surface contour section (234) formed at least by an upper surface section (230) of the rigid leading edge surface profile contour (212) and by a top surface (222) of the central lifting section (220). The rigid leading edge surface profile contour (212) is adapted to the central lifting section (220) such that at a first leading edge flap angle, the lower surface contour section (232) exhibits C1- and/or C2-continuity; and at a second leading edge flap angle, the upper surface contour section (234) exhibits C1- and/or C2-continuity. The present invention also relates to a lifting structure (W), such as a wing, comprising such an airfoil (200), and to a sailplane comprising such an airfoil (200).


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    Titel :

    DOUBLE FLAP LAMINAR AIRFOIL


    Weitere Titelangaben:

    LAMINARE DOPPELKLAPPENFLÜGELSCHAUFEL
    PROFIL AÉRODYNAMIQUE LAMINAIRE À DOUBLE VOLET


    Beteiligte:

    Erscheinungsdatum :

    16.10.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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