Rotor blade for a helicopter, comprising: a blade root, a blade tip region, a leading edge, and a trailing edge, wherein, in the blade tip region, the leading edge faces towards a rotational direction and the trailing edge faces away from the rotational direction, wherein the leading edge in the blade tip region is inclined in relation to a longitudinal extension direction of the rotor blade with respect to the rotational direction, wherein, in a region at the trailing edge in the blade tip region, an actuator arrangement is disposed which is designed to geometrically deform the blade tip region in a region of the trailing edge, characterised in that the actuator arrangement comprises: a first actuator in a first region lying in the region of the rotor blade tip, wherein a length changing direction of the first actuator extends substantially in the longitudinal extension direction, a second actuator in a second region lying in the direction of a rotor blade root with respect to the first region, wherein a length changing direction of the second actuator extends substantially in a direction transverse to the longitudinal extension direction in a rotational plane, and a third actuator in a third region (B, C) lying between the first region and the second region and having two stratified length changing directions (101, 102) which lie transversely with respect to one another. a blade root, a blade tip region, a leading edge, and a trailing edge, wherein, in the blade tip region, the leading edge faces towards a rotational direction and the trailing edge faces away from the rotational direction, wherein the leading edge in the blade tip region is inclined in relation to a longitudinal extension direction of the rotor blade with respect to the rotational direction, wherein, in a region at the trailing edge in the blade tip region, an actuator arrangement is disposed which is designed to geometrically deform the blade tip region in a region of the trailing edge, characterised in that the actuator arrangement comprises: a first actuator in a first region lying in the region of the rotor blade tip, wherein a length changing direction of the first actuator extends substantially in the longitudinal extension direction, a second actuator in a second region lying in the direction of a rotor blade root with respect to the first region, wherein a length changing direction of the second actuator extends substantially in a direction transverse to the longitudinal extension direction in a rotational plane, and a third actuator in a third region (B, C) lying between the first region and the second region and having two stratified length changing directions (101, 102) which lie transversely with respect to one another. a first actuator in a first region lying in the region of the rotor blade tip, wherein a length changing direction of the first actuator extends substantially in the longitudinal extension direction, a second actuator in a second region lying in the direction of a rotor blade root with respect to the first region, wherein a length changing direction of the second actuator extends substantially in a direction transverse to the longitudinal extension direction in a rotational plane, and a third actuator in a third region (B, C) lying between the first region and the second region and having two stratified length changing directions (101, 102) which lie transversely with respect to one another.