The rotor blade (2) has an aerodynamically acting blade profile, a movable bearing-less, joint-less rotor blade flap (4), and at least one upper and at least one lower thin inherently stable, elastically flexible and/or bendable blade skin (4a,4b). The blade skins in the profile depth direction are interconnected by their respective one side and form a rotor blade profile end section (6). By their respective other side in the profile thickness direction are spaced apart and fastened on a torsional and bend resistant profile component (8) and together with this form the rotor blade profile. A flat, length-adjustable actuator (10a,10b) is connected to one of the blade skins and can elastically extend it in the profile depth direction, and interacting with the other blade skin induces a deflection of the rotor blade flap. An independent claim is included for a rotary wing aircraft, and especially a helicopter, including at least one rotor with at least one modified rotor blade.
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