A method for manufacturing a leading edge of an aircraft lifting surface, the leading edge having a leading edge skin and a supporting structure including at least two spars span-wise arranged and fixed internally to the leading edge skin. In the method of the invention, the supporting structure is obtained from a single laminate of plies of composite material, which is conformed in such that in a cross-sectional view, the laminate includes a trapezoidal configuration which forms a front spar and a rear spar of the supporting structure. A leading edge obtained by the above-described method is disclosed. Since the supporting structure of the leading edge is obtained from a single component, namely the laminate, the manufacturing method is simplified and production costs are significantly reduced.