A leading edge structure (11) for a flow control system of an aircraft (1) including a leading edge panel (13) surrounding a plenum (17) that extends in a span direction (19). The leading edge panel (13) has a first side portion (21) extending from a leading edge point (23) to a first attachment end (25) and 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).


    Access

    Download


    Export, share and cite



    Title :

    LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT


    Contributors:

    Publication date :

    2020-04-16


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT

    HÖFT MICHAEL / NIELSEN FRANK | European Patent Office | 2021

    Free access

    Leading edge structure for a flow control system of an aircraft

    BERTOLINI IVANO / OBERMAIER MARTIN / HÖFT MICHAEL et al. | European Patent Office | 2024

    Free access

    Leading edge structure for a flow control system of an aircraft

    BERTOLINI IVANO / GIAQUINTO STEFANO / WELZ SEBASTIAN et al. | European Patent Office | 2024

    Free access

    LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT

    BERTOLINI IVANO / GIAQUINTO STEFANO / WELZ SEBASTIAN et al. | European Patent Office | 2022

    Free access

    LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT

    BERTOLINI IVANO / GIAQUINTO STEFANO / WELZ SEBASTIAN et al. | European Patent Office | 2022

    Free access