An aircraft (10) including a fuselage (20) and an aft engine (200) is provided. The fuselage (20) extends from a forward end (14) of the aircraft (10) towards an aft end (16) of the aircraft (10). The aft engine (200) is mounted to the fuselage (20) proximate the aft end (16) of the aircraft (10) and includes a fan (222) and a nacelle (224). The fan (222) is rotatable about a central axis (220) of the aft engine (200) and includes a plurality of fan blades (228). The nacelle (224) of the aft engine (200) surrounds the plurality of fan blades (228) and defines a bottom portion (248) having a forward end (14). Additionally, the nacelle (224) defines a curved surface at the forward end (14) of the bottom portion (248), the curved surface including a reference point where the curved surface defines the smallest radius of curvature (266). The nacelle (224) further defines a normal reference line (268) extending normal from the reference point. The normal reference line (268) defines an angle with the central axis (220) of the aft engine (200) greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine (200).


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    Titel :

    AFT ENGINE NACELLE SHAPE FOR AN AIRCRAFT


    Weitere Titelangaben:

    HECKTRIEBWERKSGONDELFORM FÜR EIN FLUGZEUG
    FORME DE FUSEAU MOTEUR ARRIÈRE POUR AVION


    Beteiligte:

    Erscheinungsdatum :

    26.10.2022


    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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