VANE FOR A TURBINE ENGINE WITH OPTIMISED ROOT AND METHOD FOR OPTIMISING A VANE PROFILE

The invention relates to a vane for a turbine engine of an aircraft comprising a blade having a lower surface and an upper surface that are connected upstream, in a direction of circulation of a gas in the turbine engine, by a leading edge and downstream by a trailing edge, the blade having a root at a radially external end and comprising a transverse head section (ST) in a plane perpendicular to a radial direction of the blade, taken at the radially external end with a first centre of gravity (G1). According to the invention, the root has a second centre of gravity (G2), which is defined in a plane parallel to the transverse head section and which is at least transversely offset from the first centre of gravity, the second centre of gravity (G2) being defined in a predetermined zone (ZG) at least partly demarcated by a first straight line (L1) and a second straight line (L2) substantially forming a V that is open towards the lower surface (10) and that comprises a peak, the orthogonal projection of which on