An aircraft comprising: a fuselage; a baseline wing (102, 500), the baseline wing (102, 500) coupled to the fuselage at a first end of the baseline wing (102, 500) and having a control surface, especially an aileron; and a wing extension (100,200) comprising a horizontal portion coupled to a second end of the baseline wing (102, 500), such that the horizontal portion is outboard of the baseline wing (102, 500); the horizontal portion that, when attached to the aircraft, is substantially parallel to the baseline wing (102, 500) of the aircraft, the wing extension further comprising at least two controllable airflow modification devices (CAMDs), controllable independently of any control surfaces (116, 118) of the baseline wing (102, 500), each comprising: - a control surface, - a controller, adapted to control the control surface of the CAMD independent of any control surfaces of the baseline wing, and - a sensor, adapted to detect flight condition data, representative of various flight conditions of the aircraft, resulting in various loads experienced on the aircraft, wherein the control surfaces of the at least two CAMDs are directly coupled to the horizontal portion of the wing extension; wherein the aircraft comprises: - linear and/or rotational sensors, micro load cells and/or strain gages mounted on the structure of the baseline wing, and/or - accelerometers mounted at multiple points in the baseline wing and/or wing extension, wherein the controller of a first CAMD of the at least two CAMDs is configured to detect an onset of a flutter condition, based on sensor information of the linear and/or rotational sensors, micro load cells and/or strain gages mounted on the structure of the baseline wing, and/or based upon sensor information of the accelerometers mounted at multiple points in the baseline wing and/or wing extension, wherein a second CAMD of the at least two CAMDs is configured to alleviate a torsional load on a wing, by the controller of the second CAMD being configured to control an adjusting of the control surface of the second CAMD based on the detected flight condition data of the sensor of the second CAMD, so as to relieve the torsional load on the wing; wherein the first CAMD is configured to alleviate the detected flutter condition on the baseline wing (102, 500), by the controller of the first CAMD being configured to control an adjusting of the control surface of the first CAMD to actively dampen the flutter. a fuselage; a baseline wing (102, 500), the baseline wing (102, 500) coupled to the fuselage at a first end of the baseline wing (102, 500) and having a control surface, especially an aileron; and a wing extension (100,200) comprising a horizontal portion coupled to a second end of the baseline wing (102, 500), such that the horizontal portion is outboard of the baseline wing (102, 500); the horizontal portion that, when attached to the aircraft, is substantially parallel to the baseline wing (102, 500) of the aircraft, the wing extension further comprising at least two controllable airflow modification devices (CAMDs), controllable independently of any control surfaces (116, 118) of the baseline wing (102, 500), each comprising: - a control surface, - a controller, adapted to control the control surface of the CAMD independent of any control surfaces of the baseline wing, and - a sensor, adapted to detect flight condition data, representative of various flight conditions of the aircraft, resulting in various loads experienced on the aircraft, - a control surface, - a controller, adapted to control the control surface of the CAMD independent of any control surfaces of the baseline wing, and - a sensor, adapted to detect flight condition data, representative of various flight conditions of the aircraft, resulting in various loads experienced on the aircraft, wherein the control surfaces of the at least two CAMDs are directly coupled to the horizontal portion of the wing extension; wherein the aircraft comprises: - linear and/or rotational sensors, micro load cells and/or strain gages mounted on the structure of the baseline wing, and/or - accelerometers mounted at multiple points in the baseline wing and/or wing extension, - linear and/or rotational sensors, micro load cells and/or strain gages mounted on the structure of the baseline wing, and/or - accelerometers mounted at multiple points in the baseline wing and/or wing extension, wherein the controller of a first CAMD of the at least two CAMDs is configured to detect an onset of a flutter condition, based on sensor information of the linear and/or rotational sensors, micro load cells and/or strain gages mounted on the structure of the baseline wing, and/or based upon sensor information of the accelerometers mounted at multiple points in the baseline wing and/or wing extension, wherein a second CAMD of the at least two CAMDs is configured to alleviate a torsional load on a wing, by the controller of the second CAMD being configured to control an adjusting of the control surface of the second CAMD based on the detected flight condition data of the sensor of the second CAMD, so as to relieve the torsional load on the wing; wherein the first CAMD is configured to alleviate the detected flutter condition on the baseline wing (102, 500), by the controller of the first CAMD being configured to control an adjusting of the control surface of the first CAMD to actively dampen the flutter.