Underwing-mounted trailing edge flaps for wings of aircraft are disclosed. A flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The flap includes a first edge, a second edge located opposite the first edge, a first surface extending between the first edge and the second edge, and a second surface located opposite the first surface and extending between the first edge and the second edge. The first edge is located rearward of the second edge when the flap is in the stowed position, and forward of the second edge when the flap is in the deployed position. A bullnose pivotally coupled to the flap at a location along the first edge pivots relative to the flap as the flap moves between the stowed and deployed positions.

An aircraft wing including a wing structure supporting a wing cover having an outer aerodynamic surface, and a pop-up spoiler unit including an actuation mechanism and a spoiler coupled to the actuation mechanism. The spoiler is moveable by the actuation mechanism to deploy through an aperture in the wing cover. The pop-up spoiler unit is mounted to the wing structure to be substantially isolated from wing bending deflections. The wing structure has a neutral plane which is substantially neither stretched nor compressed during bending of the wing structure. The pop-up spoiler unit is mounted to the wing structure at only two pin joints each having a respective pin axis about which the pop-up spoiler unit is substantially free to rotate, and each pin axis substantially lies in the neutral plane.

An aircraft wing including a wing structure supporting a wing cover having an outer aerodynamic surface, and a pop-up spoiler unit including an actuation mechanism and a spoiler coupled to the actuation mechanism. The spoiler is moveable by the actuation mechanism to deploy through an aperture in the wing cover. The pop-up spoiler unit is mounted to the wing structure to be substantially isolated from wing bending deflections. The wing structure has a neutral plane which is substantially neither stretched nor compressed during bending of the wing structure. The pop-up spoiler unit is mounted to the wing structure at only two pin joints each having a respective pin axis about which the pop-up spoiler unit is substantially free to rotate, and each pin axis substantially lies in the neutral plane.

Example actuator assemblies to deploy aircraft leading edge flaps and seals for aircraft leading edge flaps are described herein. An example apparatus includes an aircraft flap that is movable between a stowed position and a deployed position. The flap includes a top panel. A notch is formed in the top panel and extends into a side of the top panel near a trailing edge of the flap. The example apparatus also includes a seal coupled to the flap. The seal is movable to cover the notch when the flap is in the deployed position.

Example articulation assemblies for retracting aircraft flap support fairing tailcones and related methods are described herein. An example flap support fairing disclosed herein includes a housing to be coupled to a bottom side of a flap on a trailing edge of a wing of an aircraft, a tailcone disposed outward from an aft end of the housing, and an articulation assembly configured to move the tailcone between an extended position in which a portion of the tailcone is disposed beyond the aft end of the housing and a retracted position in which the portion of the tailcone is disposed within the housing.

A high lift system for an aircraft includes at least one lift flap arranged on a wing forming a gap between a leading edge of the wing and a trailing edge of the lift flap in an extended position of the lift flap, and at least one flap adjustment mechanism for moving the lift flap between a retracted and at least one extended position relative to the wing. The wing includes a depression with a leading depression edge for accommodating the lift flap in a retracted position, and arranged in such an area of the wing that a correspondingly formed trailing edge region of the lift flap includes a curvature, by which the gap between the leading edge of the wing and trailing edge of the lift flap is convergent. A convergent and improved gap increases the efficiency of a high lift system without any active or movable means.

A high lift system for an aircraft includes at least one lift flap arranged on a wing forming a gap between a leading edge of the wing and a trailing edge of the lift flap in an extended position of the lift flap, and at least one flap adjustment mechanism for moving the lift flap between a retracted and at least one extended position relative to the wing. The wing includes a depression with a leading depression edge for accommodating the lift flap in a retracted position, and arranged in such an area of the wing that a correspondingly formed trailing edge region of the lift flap includes a curvature, by which the gap between the leading edge of the wing and trailing edge of the lift flap is convergent. A convergent and improved gap increases the efficiency of a high lift system without any active or movable means.

Integrated slat chine apparatus and methods are described. An example apparatus includes a chine and a slat. The chine is coupled to an airfoil. The chine includes a lateral surface. The slat is located adjacent the lateral surface of the chine and coupled to the airfoil. The slat is movable relative to the airfoil between a stowed position and a deployed position. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

Integrated slat chine apparatus and methods are described. An example apparatus includes a chine and a slat. The chine is coupled to an airfoil. The chine includes a lateral surface. The slat is located adjacent the lateral surface of the chine and coupled to the airfoil. The slat is movable relative to the airfoil between a stowed position and a deployed position. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

Krueger flap apparatus and methods incorporating a bullnose having a contour variation along a spanwise direction are described. An example apparatus includes a Krueger flap having a bullnose extending in a spanwise direction. The bullnose includes a contour variation formed by a plurality of protuberances located along the bullnose. Respective ones of the protuberances are spaced along the spanwise direction.