A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.


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    Titel :

    FLOW BODY FOR AN AIRCRAFT HAVING A SOLID TRAILING-EDGE COMPONENT


    Weitere Titelangaben:

    STRÖMUNGSKÖRPER FÜR EIN FLUGZEUG MIT MASSIVER EINTRITTSKANTENKOMPONENTE
    ÉLÉMENT AÉRODYNAMIQUE POUR UN AÉRONEF COMPORTANT UN COMPOSANT DE BORD DE FUITE PLEIN


    Beteiligte:
    ERBAN MARCUS (Autor:in) / BENSMANN STEFAN (Autor:in) / FEES MARTIN (Autor:in)

    Erscheinungsdatum :

    2022-04-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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