An exposed main landing gear (26) cavity (48, 70) in a bottom wall of an aircraft fuselage (12) may include a main landing gear cavity outer ring (74) recessed within the fuselage and having an inner surface (76) encircling the main landing gear cavity, first baffle (84) extending inward from the outer ring inner surface at an aft and inboard position on the inner surface, and a second baffle (86) extending inward from the outer ring inner surface at an aft and outboard position on the outer ring inner surface. The main landing gear cavity may further include an aft fairing (58) disposed proximate the outer ring bottom edge of the outer ring and connected to the fuselage at an aft side of the main landing gear cavity. An aft fairing top surface (94) may have curvature causing the top surface to extend downward away from the outer ring as the top surface extends inward away from the outer ring.


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    Titel :

    DRAG REDUCTION DEVICE FOR EXPOSED LANDING GEAR CAVITIES


    Weitere Titelangaben:

    WIDERSTANDSVERMINDERUNGSVORRICHTUNG FÜR FREILIEGENDE FAHRWERKSHOHLRÄUME
    DISPOSITIF DE RÉDUCTION DE TRAÎNÉE POUR CAVITÉS DE TRAIN D'ATTERRISSAGE EXPOSÉES


    Beteiligte:
    ADAMSON ERIC E (Autor:in) / TREIBER DAVID A (Autor:in)

    Erscheinungsdatum :

    2020-02-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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