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A laminar flow control aircraft wing combines suction surfaces and slots in its leading and trailing edge regions, with natural laminar flow over its main box region to achieve laminar boundary layer flow over a majority of the wing surface area. The wing includes a leading edge flap that is used to

A laminar flow control aircraft wing combines suction surfaces and slots in its leading and trailing edge regions, with natural laminar flow over its main box region to achieve laminar boundary layer flow over a majority of the wing surface area. The wing includes a leading edge flap that is used to protect the leading edge region of the wing from insect accumulation and surface erosion caused by the impact of dirt, rain, or other airborne materials when the leading edge flap is deployed in a low-speed position. At high aircraft speeds, the leading edge flap is stored in the surface of the leading edge region of the wing and forms part of the suction system for that area of the wing. The wing also includes a flexible trailing edge suction surface spoiler system that allows the spoilers to bend either upwardly for lateral control or downwardly when the trailing edge flap is deployed into a low-speed position.

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A laminar flow control airfoil having an upper surface, a lower surface, a leading edge, a trailing edge, a tip, and a root, said airfoil including front and rear spars that chordwise divide said airfoil into a leading edge region, a main box region, and a trailing edge region, said leading edge reg

A laminar flow control airfoil having an upper surface, a lower surface, a leading edge, a trailing edge, a tip, and a root, said airfoil including front and rear spars that chordwise divide said airfoil into a leading edge region, a main box region, and a trailing edge region, said leading edge region extending between said leading edge and said front spar, said main box region extending aft of said leading edge region between said front and rear spars, said trailing edge region extending aft of said main box region between said rear spar and said trailing edge, said airfoil including suction means internal thereto for applying suction to portions of said leading and trailing edge regions to remove boundary layer air flowing thereover, each of the upper and lower surfaces of said airfoil being contoured to provide a chordwise pressure distribution having a negative gradient rising steeply from a positive pressure value at an attachment line position adjacent the leading edge to a peak negative value at a peak position located immediately aft of said leading edge, a positive gradient from said peak position aft to said front spar, a negative gradient from said front spar aft to said rear spar, and positive recoveries from said rear spar aft to said trailing edge.