The invention provides a leading edge (1) for an airfoil of an aircraft comprising a leading plate (2) with a convex side (21) and a concave side (22), at least one container (3) filled with a non-Newtonian fluid, wherein the leading edge is configured to be secured to the torsion box (10) of the airfoil, the at least one container (3) being arranged between the concave side (22) of the leading plate (2) and the torsion box (10) of the airfoil. The invention also provides an airfoil comprising such leading edge and a method for assembling such leading edge.
LEADING EDGE FOR AN AIRFOIL
VORDERKANTE FÜR EINE TRAGFLÄCHE
BORD D'ATTAQUE POUR UN PROFIL AÉRODYNAMIQUE
2022-02-09
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |