Method for manufacturing a leading edge section with hybrid laminar flow control for an aircraft, the method comprising the steps of: • providing a plurality of elongated modules, • providing an inner mandrel shaped with an inner surface of an aerodynamic leading edge profile, • providing an outer hood shaped with an outer surface of the aerodynamic leading edge profile, • providing first and second C-shaped profiles (5, 7) comprising a plurality of passing-through cavities configured to receive the modules, • assembling an injection moulding tool, comprising: ∘ placing the first profile on a first end of the inner mandrel, and the second profile on a second end of the inner mandrel, both profiles (5, 7) contacting the inner mandrel, ∘ arranging a first extreme of each elongated module in one cavity of the first profile, and a second extreme of said module in another cavity of the second profile, both cavities positioned in a same radial direction, and such arrangement leaving a lower gap defining the thickness of the inner surface of the leading edge section, ∘ placing the hood on the first and second profiles (5, 7) to close the tool, leaving an upper gap defining the thickness of the outer surface of the leading edge section, • closing the injection moulding tool, • filling the closed injection moulding tool with an injection compound comprising resin and a reinforcing additive, • demoulding after the hardening of the injection compound to obtain a leading edge section, and • perforating the outer and the inner surface of said leading edge section to finally obtain a leading edge section with hybrid laminar flow control. • providing a plurality of elongated modules, • providing an inner mandrel shaped with an inner surface of an aerodynamic leading edge profile, • providing an outer hood shaped with an outer surface of the aerodynamic leading edge profile, • providing first and second C-shaped profiles (5, 7) comprising a plurality of passing-through cavities configured to receive the modules, • assembling an injection moulding tool, comprising: ∘ placing the first profile on a first end of the inner mandrel, and the second profile on a second end of the inner mandrel, both profiles (5, 7) contacting the inner mandrel, ∘ arranging a first extreme of each elongated module in one cavity of the first profile, and a second extreme of said module in another cavity of the second profile, both cavities positioned in a same radial direction, and such arrangement leaving a lower gap defining the thickness of the inner surface of the leading edge section, ∘ placing the hood on the first and second profiles (5, 7) to close the tool, leaving an upper gap defining the thickness of the outer surface of the leading edge section, ∘ placing the first profile on a first end of the inner mandrel, and the second profile on a second end of the inner mandrel, both profiles (5, 7) contacting the inner mandrel, ∘ arranging a first extreme of each elongated module in one cavity of the first profile, and a second extreme of said module in another cavity of the second profile, both cavities positioned in a same radial direction, and such arrangement leaving a lower gap defining the thickness of the inner surface of the leading edge section, ∘ placing the hood on the first and second profiles (5, 7) to close the tool, leaving an upper gap defining the thickness of the outer surface of the leading edge section, • closing the injection moulding tool, • filling the closed injection moulding tool with an injection compound comprising resin and a reinforcing additive, • demoulding after the hardening of the injection compound to obtain a leading edge section, and • perforating the outer and the inner surface of said leading edge section to finally obtain a leading edge section with hybrid laminar flow control.