A rotor (3, 5) for a hover-capable aircraft, comprising: - a hub (6, 8); and - a plurality of blades (7, 14) hinged on said hub (6, 8); each said blade (7, 14) extending along a first axis and, in turn, comprising: - a leading edge and a trailing edge, opposite to each other; - a top surface and a bottom surface, opposite to each other and extending between said leading edge and said trailing edge; - a chord joining the points of said leading edge and said trailing edge in a section of said blade (7, 14) orthogonal to said axis; and - a closed shell made of composite material and adapted to withstand the torque directed along said axis of said blade (7, 14); said shell comprising: - a first and a second element (31, 32), separate from each other, delimiting the respective said shell on mutually opposite sides and respectively arranged at said top surface and said bottom surface of the respective said blade (7, 14); said first and second elements (31, 32) of each said blade (7, 14) comprising respective first ends (37, 38) arranged on the side of the associated leading edge and spaced apart from each other; - a first connection element arranged on the side of the associated leading edge and interposed between said first ends (37, 38) of the respective first and second elements (31, 32); and - a third element connected to the associated said first and second elements (31, 32) and arranged on the side of the leading edge; said first connection element being connected to respective first faces of said first and second elements (31, 32); said first faces being respectively arranged on the opposite side of said top surface and on the opposite side of said bottom surface of said blade; said blade (7, 14) further comprising a fourth element interposed between said third element and said first connection element; characterized in that said third element is connected to respective second faces opposite to corresponding said first faces of said first and second elements (31, 32); said first and second elements (31, 32) of each said blade (7, 14) respectively having, at least in part, a lie substantially parallel to a lie of the corresponding said top surface and bottom surface of the blade (7, 14); said first and second elements (31, 32) of each said blade (7, 14) having a thickness in the transverse direction to the lie of the respective said top surface and bottom surface; said first and second elements (31, 32) respectively comprising a first and a second portion opposite to each other and having greater thickness than the respective remaining parts of the respective said second and third elements (31, 32); the extension of said portions parallel to said chord in said section ranging between 30% and 35% of the length of said chord in said section. - a hub (6, 8); and - a plurality of blades (7, 14) hinged on said hub (6, 8); - a leading edge and a trailing edge, opposite to each other; - a top surface and a bottom surface, opposite to each other and extending between said leading edge and said trailing edge; - a chord joining the points of said leading edge and said trailing edge in a section of said blade (7, 14) orthogonal to said axis; and - a closed shell made of composite material and adapted to withstand the torque directed along said axis of said blade (7, 14); - a first and a second element (31, 32), separate from each other, delimiting the respective said shell on mutually opposite sides and respectively arranged at said top surface and said bottom surface of the respective said blade (7, 14); said first and second elements (31, 32) of each said blade (7, 14) comprising respective first ends (37, 38) arranged on the side of the associated leading edge and spaced apart from each other; - a first connection element arranged on the side of the associated leading edge and interposed between said first ends (37, 38) of the respective first and second elements (31, 32); and - a third element connected to the associated said first and second elements (31, 32) and arranged on the side of the leading edge;