A free-streamline airfoil includes a front portion, the front portion including a leading edge geometry configured to force a sudden separation of the flow, and a contoured

A flight control surface with an actuator with an aerodynamic fairing for a swept aircraft wing. The swept aircraft wing includes a movable flight control surface with a hinge line non-perpendicular to the line of flight of the aircraft, and an actuator arm configured to actuate the flight control surface. The actuator arm includes a longitudinal axis substantially aligned with the line of flight, the actuator arm extending at least partially from an outer surface of the aircraft wing, and a fairing arranged on the outer surface of the aircraft wing to at least partially cover the actuator arm. Aligning the actuator arm with the line of flight of the aircraft may allow for an improved fairing to be provided.

A flight control surface with an actuator with an aerodynamic fairing for a swept aircraft wing. The swept aircraft wing includes a movable flight control surface with a hinge line non-perpendicular to the line of flight of the aircraft, and an actuator arm configured to actuate the flight control surface. The actuator arm includes a longitudinal axis substantially aligned with the line of flight, the actuator arm extending at least partially from an outer surface of the aircraft wing, and a fairing arranged on the outer surface of the aircraft wing to at least partially cover the actuator arm. Aligning the actuator arm with the line of flight of the aircraft may allow for an improved fairing to be provided.

Transitioning quadcopters and tricopters use passively adjusting tiltwings to reduce the number of actuators needed to control flight. Both transitioning copters can operate with four controlled actuators comprising four motor speeds for the quadcopter and three motor speeds and one rudder position for the tricopter.

Transitioning quadcopters and tricopters use passively adjusting tiltwings to reduce the number of actuators needed to control flight. Both transitioning copters can operate with four controlled actuators comprising four motor speeds for the quadcopter and three motor speeds and one rudder position for the tricopter.

A folding multi-rotor VTOL aircraft is described that stows the rotor propulsion system in the region above the fuselage and fit within the length and width of the fuselage footprint. The folding members supporting the rotor propulsion units then fit within the regions between the stowed rotor diameters. The members are of sufficient length that when unfolded to operational configuration the slipstream of the rotors do not impinge on the fuselage. Overall aircraft height includes the fuselage, the stowed rotors, and a powered landing gear that provides ground mobility and short take-off and emergency landing capabilities. The overall height is minimized by a compact rotor system and low or adjustable landing gear ground clearance. The rotor propulsion units may incorporate ducts that are specially designed to produce improved lift.

A folding multi-rotor VTOL aircraft is described that stows the rotor propulsion system in the region above the fuselage and fit within the length and width of the fuselage footprint. The folding members supporting the rotor propulsion units then fit within the regions between the stowed rotor diameters. The members are of sufficient length that when unfolded to operational configuration the slipstream of the rotors do not impinge on the fuselage. Overall aircraft height includes the fuselage, the stowed rotors, and a powered landing gear that provides ground mobility and short take-off and emergency landing capabilities. The overall height is minimized by a compact rotor system and low or adjustable landing gear ground clearance. The rotor propulsion units may incorporate ducts that are specially designed to produce improved lift.

A wing system (2) for an aircraft includes a movable flow body (6) and a cover panel (8), wherein the flow body (6) and the cover panel (8) both are movably supported on a main wing body (4). While the flow body (6) is actively driven into upwards or downwards deflected positions, the cover panel (8) is coupled with the flow body (6) to follow its motion. The cover panel covers a part of the flow body (6) and the main wing body (4) in order to provide a substantially continuous, closed outer contour.

A helicopter has a fuselage, a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing extending from the fuselage on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system.

A helicopter has a fuselage, a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing extending from the fuselage on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system.