Aircraft comprising - an aircraft body defining a longitudinal direction, a vertical direction, and a transverse direction, the longitudinal direction corresponding to the direction from the tail to the nose of the aircraft, the vertical direction corresponding to the direction of the earth's gravitational force when the aircraft is resting on the ground, and the transverse direction being perpendicular to the longitudinal direction and the vertical direction; and - at least two propulsion devices (1, 1F, 1R), each rotatable about an associated axis of rotation to generate a respective associated thrust vector (701, 702); wherein a first number of the propulsion devices is arranged along a first straight line parallel to the transverse direction, and a second number of the propulsion devices is arranged along a second straight line parallel to the transverse direction, the first straight line is spaced apart from the second straight line, and the center of mass of the aircraft is positioned with respect to the longitudinal direction between the first straight line and the second straight line; wherein the aircraft is adapted to perform a hover flight in which all forces acting on the aircraft and all torques acting on the aircraft with respect to the center of mass of the aircraft substantially disappear, characterized in that in the hover flight - each of the associated axes of rotation is oriented substantially in the transverse direction of the aircraft body, and - each of the at least two propulsion devices (1, 1F, 1R) rotates substantially in the same direction of rotation about the respective associated axis of rotation. - an aircraft body defining a longitudinal direction, a vertical direction, and a transverse direction, the longitudinal direction corresponding to the direction from the tail to the nose of the aircraft, the vertical direction corresponding to the direction of the earth's gravitational force when the aircraft is resting on the ground, and the transverse direction being perpendicular to the longitudinal direction and the vertical direction; and - at least two propulsion devices (1, 1F, 1R), each rotatable about an associated axis of rotation to generate a respective associated thrust vector (701, 702); wherein a first number of the propulsion devices is arranged along a first straight line parallel to the transverse direction, and a second number of the propulsion devices is arranged along a second straight line parallel to the transverse direction, the first straight line is spaced apart from the second straight line, and the center of mass of the aircraft is positioned with respect to the longitudinal direction between the first straight line and the second straight line; a first number of the propulsion devices is arranged along a first straight line parallel to the transverse direction, and a second number of the propulsion devices is arranged along a second straight line parallel to the transverse direction, the first straight line is spaced apart from the second straight line, and the center of mass of the aircraft is positioned with respect to the longitudinal direction between the first straight line and the second straight line; - each of the associated axes of rotation is oriented substantially in the transverse direction of the aircraft body, and - each of the at least two propulsion devices (1, 1F, 1R) rotates substantially in the same direction of rotation about the respective associated axis of rotation.