Leading Edge For An Aircraft Lifting Surface

The present invention refers to a leading edge for an aircraft lifting surface, at one aspect, provides an optimized leading edge (1) for an aircraft lifting or supporting surfaces, such as wings and stabilizers, wherein the leading edge comprises inboard and outboard leading edge sections (2,3) span-wise arranged so as to form together an aerodynamic surface (4) of the leading edge, each of said leading edge sections (2,3), comprising a skin panel (5,6) and a support structure (7,8) formed by spars (9, 10, 11, 14) internally arranged in the skin panel. These two support structures are designed taking into account the different load requirements of those two different sections, so that the number of spars in each leading edge section, is progressively reduced from root to tip of the leading edge, in such a way that the support structure (7) of the outboard leading edge section (3), has less spars than the support structure (8) of the inboard leading edge section (2), hence the weight of the leading edge is reduced but maintaining the required structural behavior.