An aircraft (100, 200, 300) comprising a fuselage (102, 202, 302) and an unducted turbine engine (10, 116, 216, 316). The fuselage having a divot (122, 222, 322) with an upstream edge (130, 330) and a downstream edge (132, 332). The divot is defined by a straight reference line (142), connecting the upstream edge and the downstream edge and having a length (L), and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core (44), a nacelle (40), and a set of blades (42, 118, 318). A first flow ratio (FR1) is equal to: h/L and wherein the first flow ratio is greater or equal to 0.01 and less than or equal to 0.15.


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    Titel :

    AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE


    Weitere Titelangaben:

    FLUGZEUG MIT EINEM RUMPF DER EINEN MANTELLOSEN TURBINENMOTOR AUFNIMMT
    AÉRONEF AVEC UN FUSELAGE LOGEANT UNE TURBOMACHINE NON CARÉNÉE


    Beteiligte:

    Erscheinungsdatum :

    13.12.2023


    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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