A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) surrounding a plenum (7). The leading edge panel (3) has a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing the plenum (7), an outer wall element (23) for contact with an ambient flow (25), a core assembly (97). The outer wall element (23) includes micro pores (31) forming a fluid connection between the core assembly (97) and the ambient flow (25). The inner wall element (21) includes openings (33) forming a fluid connection between the core assembly (97) and the plenum (7). The outer wall element (23) extends from the first attachment end (17) to the second attachment end (19).


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    Title :

    Leading edge structure for a flow control system of an aircraft


    Contributors:

    Publication date :

    2024-04-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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