A rotor for a hover-capable aircraft , comprising: - a hub ; and - a plurality of blades hinged on said hub ; each said blade extending along a first axis (B) 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 (S) of said blade orthogonal to said axis (B); and - a closed shell made of composite material and adapted to withstand the torque directed along said axis (B) of said blade ; said shell comprising: - a first and a second element , 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 ; said first and second elements of each said blade comprising respective first ends 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 of the respective first and second elements ; and - a third element connected to the associated said first and second elements 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 ; 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 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 ; said first and second elements of each said blade 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 ; said first and second elements of each said blade having a thickness in the transverse direction to the lie of the respective said top surface and bottom surface ; said first and second elements 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 ; the extension (L) of said portions parallel to said chord in said section (S) ranging between 30% and 35% of the length (M) of said chord in said section (S). - a hub ; and - a plurality of blades hinged on said hub ; - 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 (S) of said blade orthogonal to said axis (B); and - a closed shell made of composite material and adapted to withstand the torque directed along said axis (B) of said blade ; - a first and a second element , 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 ; said first and second elements of each said blade comprising respective first ends 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 of the respective first and second elements ; and - a third element connected to the associated said first and second elements and arranged on the side of the leading edge ; <EOS>