A wing includes a main wing element, a flap disposed on a rear side of the main wing element, a storage section disposed in the main wing element to retract the flap, fairings each of which is disposed under the storage section and covers a flap-moving mechanism for moving the flap, and a shielding member which is disposed in the storage section at a position between the fairings and blocks air flowing in the storage section in the wing span direction. With this configuration, the shielding member disposed in the storage section can block a fluctuating airflow before pressure fluctuations occur in a feedback manner within the storage section. As a result, it is possible to suppress the occurrence of self-excited vibrations, and to suppress large pressure fluctuations at specific frequencies.

A wing includes a main wing element, a flap disposed on a rear side of the main wing element, a storage section disposed in the main wing element to retract the flap, fairings each of which is disposed under the storage section and covers a flap-moving mechanism for moving the flap, and a shielding member which is disposed in the storage section at a position between the fairings and blocks air flowing in the storage section in the wing span direction. With this configuration, the shielding member disposed in the storage section can block a fluctuating airflow before pressure fluctuations occur in a feedback manner within the storage section. As a result, it is possible to suppress the occurrence of self-excited vibrations, and to suppress large pressure fluctuations at specific frequencies.

An aircraft wing has a flap arrangement with an inboard flap configured to move in a chordwise extension direction relative to the wing, the inboard flap having an outboard side, and an outboard flap adjacent to the inboard flap and configured to move in the chordwise extension direction relative to the wing, the outboard flap including an inboard side. A flap interconnect between the inboard flap and outboard flap has a roller mounted to a pin extending from the outboard side of the inboard flap and a guide track extending from the inboard side of the outboard flap. The guide track engages the roller on the inboard flap to limit deflection of the outboard flap relative to the inboard flap during movement of the inboard flap in the chordwise extension direction and movement of the outboard flap in the chordwise extension direction, to provide relative alignment of the inboard flap and outboard flap.

An aircraft wing has a flap arrangement with an inboard flap configured to move in a chordwise extension direction relative to the wing, the inboard flap having an outboard side, and an outboard flap adjacent to the inboard flap and configured to move in the chordwise extension direction relative to the wing, the outboard flap including an inboard side. A flap interconnect between the inboard flap and outboard flap has a roller mounted to a pin extending from the outboard side of the inboard flap and a guide track extending from the inboard side of the outboard flap. The guide track engages the roller on the inboard flap to limit deflection of the outboard flap relative to the inboard flap during movement of the inboard flap in the chordwise extension direction and movement of the outboard flap in the chordwise extension direction, to provide relative alignment of the inboard flap and outboard flap.

A lifting surface of an aircraft, comprising a leading edge and a notch located in the leading edge. The notch comprises two walls adapted to be parallel to the direction of the incident flow to the lifting surface and a third wall adapted to face the incident flow to the lifting surface when it is in flight. The lifting surface also comprises a retractable cover element, the notch and the retractable cover element being configured such that when the retractable cover element does not cover the notch, the notch is exposed to the incident flow generating a vortex which increases the lift force of the lifting surface, delaying stall.

A lifting surface of an aircraft, comprising a leading edge and a notch located in the leading edge. The notch comprises two walls adapted to be parallel to the direction of the incident flow to the lifting surface and a third wall adapted to face the incident flow to the lifting surface when it is in flight. The lifting surface also comprises a retractable cover element, the notch and the retractable cover element being configured such that when the retractable cover element does not cover the notch, the notch is exposed to the incident flow generating a vortex which increases the lift force of the lifting surface, delaying stall.

Methods and devices to measure an angular deflection of an aircraft member. The devices are configured to be attached to the aircraft member. The devices are configured to obtain an orientation of the device about three separate axes. The methods use initial orientation values and dynamic orientation values to calculate an axis of rotation. Using the axis of rotation, the deflection angle can be calculated for the aircraft member.

Methods and devices to measure an angular deflection of an aircraft member. The devices are configured to be attached to the aircraft member. The devices are configured to obtain an orientation of the device about three separate axes. The methods use initial orientation values and dynamic orientation values to calculate an axis of rotation. Using the axis of rotation, the deflection angle can be calculated for the aircraft member.

A gurney flap arrangement includes: an airfoil 2 with a trailing edge 6 and an opening 14 in a surface 8 of the airfoil 2; a gurney flap 1 having a first position in which at least a portion of the gurney flap 1 extends through the opening 14 and projects outwardly from the airfoil surface 8, and a second position in which the gurney flap 1 does not project from the airfoil surface 8 or projects outwardly from the airfoil surface 8 to a lesser extent; and a gurney flap actuator 3 for moving the gurney flap 1 between at least the first position and the second position.

A gurney flap arrangement includes: an airfoil 2 with a trailing edge 6 and an opening 14 in a surface 8 of the airfoil 2; a gurney flap 1 having a first position in which at least a portion of the gurney flap 1 extends through the opening 14 and projects outwardly from the airfoil surface 8, and a second position in which the gurney flap 1 does not project from the airfoil surface 8 or projects outwardly from the airfoil surface 8 to a lesser extent; and a gurney flap actuator 3 for moving the gurney flap 1 between at least the first position and the second position.