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).
LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT
2020-04-16
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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