An aircraft with wings (1; 1 a, 1 b) and a system for minimizing the influence of unsteady flow states, wherein the wing consists of a respective main wing and at least one control flap adjustably arranged relative thereto, an adjusting drive for activating the at least one control flap, as well as a sensor arrangement for acquiring the setting position of the control flap, and the aircraft further exhibits: • a presetting device for generating desired parameters corresponding to flight states of the aircraft, • a flight state sensor arrangement for generating flight state data, and • a flight control device, which is functionally connected with the presetting device, the adjusting drive and the sensor arrangement for acquiring the setting position of the control flap, so as to adjust the aircraft to the flight states corresponding to the desired parameters, wherein • the system for minimizing the influence of unsteady flow states exhibits at least one arrangement of flow-influencing devices for influencing the fluid flow over a surface segment, which are functionally connected with the flight control device, and incorporated in at least one surface segment (10; 11 a, 12a; 11 b, 12b) of the main wing of each wing (M; 1 a, 1 b) extending in a respective wingspan direction and/or of at least one control flap and/or incorporated in at least one surface segment of at least a trailing edge flap of each wing (M; 1 a, 1 b) extending in a respective wingspan direction, and/or • the wing further comprises at least one trailing edge flap (4a, 4b) and the system for minimizing the influence of unsteady flow states exhibits at least one arrangement of flow-influencing devices for influencing the fluid flow over a surface segment, which are functionally connected with the flight control device, and incorporated in at least one surface segment of the trailing edge flap (4a, 4b) of each wing (M; 1 a, 1 b) extending in a respective wingspan direction, and wherein the system for minimizing the influence of unsteady flow states further exhibits a detection device for detecting unsteady flow states acting on the aircraft, characterized in that the system for minimizing the influence of unsteady flow states further exhibits an actuating function that is functionally connected with the flow-influencing devices to influence the flow in the different segments of a wing (1; 1 a, 1 b), designed in such a way that the latter, based on the unsteady flow states detected by the detection device and setting position of the control flap acquired by the sensor arrangement, actuate the flow-influencing devices so as to minimize the influence of unsteady free flow states on the aircraft. • a presetting device for generating desired parameters corresponding to flight states of the aircraft, • a flight state sensor arrangement for generating flight state data, and • a flight control device, which is functionally connected with the presetting device, the adjusting drive and the sensor arrangement for acquiring the setting position of the control flap, so as to adjust the aircraft to the flight states corresponding to the desired parameters, • the system for minimizing the influence of unsteady flow states exhibits at least one arrangement of flow-influencing devices for influencing the fluid flow over a surface segment, which are functionally connected with the flight control device, and incorporated in at least one surface segment (10; 11 a, 12a; 11 b, 12b) of the main wing of each wing (M; 1 a, 1 b) extending in a respective wingspan direction and/or of at least one control flap and/or incorporated in at least one surface segment of at least a trailing edge flap of each wing (M; 1 a, 1 b) extending in a respective wingspan direction, and/or • the wing further comprises at least one trailing edge flap (4a, 4b) and the system for minimizing the influence of unsteady flow states exhibits at least one arrangement of flow-influencing devices for influencing the fluid flow over a surface segment, which are functionally connected with the flight control device, and incorporated in at least one surface segment of the trailing edge flap (4a, 4b) of each wing (M; 1 a, 1 b) extending in a respective wingspan direction, and