An aerodynamic structure 1 (e.g. aerofoil) comprising a leading edge part 15 fixed to a structural torsion box 10 front side. An air inlet 17 on the leading edge part surface enables air flow into the aerodynamic structure interior. A spanwise extending duct 19 is comprised within the torsion box (e.g. aeroplane wing box) and fluidly connects the air inlet to an air outlet. The outlet is spaced apart from the inlet along a spanwise direction. Optionally, the duct is integrated with a component of the torsion box, e.g. front spar 11, upper 13 or lower 14 cover. The air inlet may comprise a plurality of air inlet slots. The aerodynamic structure (aircraft wing or tailplane) may comprise a porous skin portion, wherein the inlet comprises pores or holes. The duct may be comprised in a hybrid laminar flow control, HLFC, system or boundary layer control system for sucking air into the inlet and expelling air out from the outlet during flight. The HLFC system may be passive (using air pressure differential between inlet and outlet) or active (comprising a pump). The leading edge part may comprise a fixed skin or a high lift device, e.g. Krueger flap or slat.


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    Title :

    Ducts for laminar flow control systems


    Contributors:

    Publication date :

    2019-04-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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