A leading-edge device for an aircraft is proposed, the device comprising a flow body having a front skin, a back skin, a spar and an air inlet, wherein the front skin is curved around a spanwise axis to form a bottom section and a top section, wherein a leading edge of the flow body is arranged between the bottom section and the top section, and wherein the spar extends from the bottom section to the top section, wherein the front skin, the back skin and the spar enclose at least one air chamber that is in fluid communication with the air inlet, wherein an outlet portion is arranged at least directly adjacent to the bottom section of the front skin, and wherein the outlet portion comprises a plurality of air outlets for letting air from the at least one air chamber exhaust through the air outlets.
LEADING-EDGE DEVICE FOR AN AIRCRAFT
VORDERKANTENVORRICHTUNG FÜR EIN FLUGZEUG
DISPOSITIF DE BORD D'ATTAQUE POUR AÉRONEF
2023-06-21
Patent
Electronic Resource
English