A nacelle (22) for a turbofan propulsion system is provided that extends along a centerline (24) and includes a forward cowling (36) and an aft cowling (38). To improve the fit of a turbofan propulsion system in the space between the wing and ground of a fixed-wing aircraft, the aft cowling (38) of the nacelle (22) is modified. The aft cowling (38) has a non-circular cross-sectional geometry disposed in a plane substantially perpendicular to the centerline (24). The non-circular cross-sectional geometry includes a radially recessed section (62) disposed between first and second curved sections (58, 60). The first and the second curved sections (58, 60) each have a radius (74, 76) that is greater than a radial distance (86) between the centerline and a center point (82) of the radially recessed section (62).


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    Titel :

    Non-circular aft nacelle cowling geometry


    Weitere Titelangaben:

    Nicht kreisförmige Heckgondelverkleidungsgeometrie
    Géométrie de carter de nacelle arrière non circulaire


    Beteiligte:

    Erscheinungsdatum :

    2017-08-02


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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