A leading edge structure (11) for a flow control system of an aircraft (1) including a leading edge panel (13) surrounding surrounds a plenum (17) which extends in a span direction (19), wherein the leading edge panel (13) has a first side portion (21) extending from a leading edge point (23) to a first attachment end (25), wherein the leading edge panel (13) has a second side portion (27) opposite the first side portion (21), extending from the leading edge point (23) to a second attachment end (29), wherein the leading edge panel (13) comprises an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), and wherein the leading edge panel (13) comprises a plurality of micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39).


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    Titel :

    Leading edge structure for a flow control system of an aircraft


    Beteiligte:

    Erscheinungsdatum :

    26.10.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F15D FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS , Strömungsdynamik, d.h. Verfahren oder Vorrichtungen zum Beeinflussen der Strömung von Gasen oder Flüssigkeiten / B64C AEROPLANES , Flugzeuge



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