Variable-pitch stator vane for an aircraft turbine engine

A variable-pitch stator vane for an aircraft turbine engine, said vane being streamlined with respect to a longitudinal axis (X), said vane comprising an airfoil blade extending along a vertical stacking axis (E) and having a common leading edge, said blade comprising:

• a central portion having in section a first skeleton line delimited transversely by said leading edge and a trailing edge, and a first chord connecting said leading edge to said trailing edge;
• a first end portion vertically delimiting said central portion, said first end portion having in section a second skeleton line transversely delimited by said leading edge and a first downstream limit, and a second chord connecting said leading edge to said first downstream limit, a total length (L2) of the second chord being between 40% and 80% of a total length (L1) of the first chord;
• and
• a first junction between said central portion and said first end portion,
• wherein a skeleton angle (α) at a first location defined by the intersection of the first skeleton line and an orthogonal projection from the first chord at a first length l1 of the first chord in a section of said central portion is defined by a first function G1(l1) and the skeleton angle (α) at a second location defined by the intersection of the second skeleton line and an orthogonal projection from the second chord at a second length l2 of the second chord in a section of said first end portion is defined by a second function G2(l2), the skeleton angle (α) corresponding in section to an angle formed between a tangent (T) to the corresponding skeleton line at the point considered and said longitudinal axis (X), the derivative function from the function G1(l1) with respect to the first length l1 being denoted G1′ (l1), the derivative function from the function G2(l2) with respect to the second length l2 being denoted G2′(l2), the absolute value of an average increment A2 of G2′(l2) between the leading edge and the first downstream limit is greater than the absolute value of an average increment A1 of G1′(l1) between the leading edge and a point P where the first length l1 from the leading edge to said point P is equal to the total length (L2) of the second chord, an average increment of a function f between a point A (a, f(a)) and a point B (b, f(b)) corresponding, by definition, to the quotient of the difference f(b)−f(a) by the difference b−a.