Method for manufacturing an aircraft leading edge panel that allows extensive laminar flow to be obtained, and leading edge comprising at least one panel obtained using the said method

A method for manufacturing an aircraft leading edge panel, the method comprising:

• placing a sheet in a cavity of a mould, the cavity delimited by a shaping surface configured to shape an exterior face of the panel that is to be obtained, the shaping surface having an optimized surface finish, wherein the optimized surface finish includes a roughness Ra and Rt of the order of 0.2 μm;
• and
• overmoulding a coating onto the sheet by injecting a material into the cavity of the mould, the coating comprising, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained, the exterior face of the coating having the optimized surface finish conferred by the shaping surface of the mould,
• wherein the sheet comprises an internal face, an external face at least partially coated with the coating and at least one through-orifice,
• wherein the coating material is injected via at least one feed positioned on the side of the internal face of the sheet and in line with the through-orifice, and
• wherein at least two feeds each comprise a nozzle having an end in raised relief with respect to a contact surface of the mould against which surface the internal face of the sheet is pressed, the end of the nozzle having shapes that complement those of the corresponding through-orifice so as to obtain a clearance-free fit between the end of the nozzle and the through-orifice.