Turbine engine blade, in particular for a one-piece bladed disk

A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip, wherein the leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in a range 20% to 40% of a total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip, wherein

• the sweep angle of the leading edge of the airfoil becomes negative as from a second radial height of the airfoil situated in a range 60% to 80% of the total radial height of the airfoil.