An aircraft wing assembly comprises a main wing portion 5 having a high-lift device 9 which is movable between a retracted position at the main wing portion and a deployed position defining a gap 37 between the high-lift device and the main wing portion. The high-lift device has a flow surface with an upper skin portion 25 and a lower skin portion 27. The flow surface of the high-lift device comprises a first flow surface portion 23, a second flow surface portion 25 and a third flow surface portion 27. The first flow surface portion is micro-perforated for an air inflow. The first flow surface portion extends on the upper skin from the leading edge in chordwise direction for 2% or less of the local chord and extends on the lower skin from the leading edge in chordwise direction for 2% or less of the local chord. The second and third flow surface portions are not micro-perforated and extend over the rest of the upper and lower skin portions respectively. Airflow is allowed to enter pores in the first flow surface and exits from an outlet 39. The outlet may include a fairing (41, fig 8).


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    Titel :

    Aircraft wing assembly


    Beteiligte:
    CHING-YU HUI (Autor:in) / CHRISTOPHER BAUER (Autor:in)

    Erscheinungsdatum :

    20.06.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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