Editing Flap (aeronautics) (section)

{{Short description|Anti-stalling high-lift device on aircraft}}
{{More citations needed|date=February 2013}}
{{Use dmy dates|date=February 2020}}
[[File:wing.slat.600pix.jpg|thumb|Trailing edge flaps extended on the right on a typical airliner (an [[Airbus A310|Airbus A310-300]]). [[Leading edge slats]] are also extended, on the left.]]

A '''flap''' is a [[high-lift device]] used to reduce the [[stall (flight)|stalling speed]] of an [[aircraft]] [[wing]] at a given weight. Flaps are usually mounted on the wing [[trailing edge]]s of a [[fixed-wing aircraft]]. Flaps are used to reduce the take-off distance and the landing distance. Flaps also cause an increase in [[Drag (physics)|drag]] so they are retracted when not needed.

The flaps installed on most aircraft are partial-span flaps; spanwise from near the wing root to the inboard end of the [[aileron]]s. When partial-span flaps are extended they alter the spanwise [[lift distribution]] on the wing by causing the inboard half of the wing to supply an increased proportion of the lift, and the outboard half to supply a reduced proportion of the lift. Reducing the proportion of the lift supplied by the outboard half of the wing is accompanied by a reduction in the [[angle of attack]] on the outboard half. This is beneficial because it increases the margin above the [[Stall (fluid dynamics)|stall]] of the outboard half, maintaining aileron effectiveness and reducing the likelihood of asymmetric stall, and [[Spin (aerodynamics)|spinning]]. The ideal lift distribution across a wing is elliptical, and extending partial-span flaps causes a significant departure from the elliptical. This increases [[lift-induced drag]] which can be beneficial during approach and landing because it allows the aircraft to descend at a steeper angle.

Extending the wing flaps increases the [[camber (aerodynamics)|camber]] or curvature of the wing, raising the maximum [[lift coefficient]] or the upper limit to the lift a wing can generate. This allows the aircraft to generate the required lift at a lower speed, reducing the minimum speed (known as stall speed) at which the aircraft will safely maintain flight. For most aircraft configurations, a useful side effect of flap deployment is a decrease in aircraft pitch angle which lowers the nose thereby improving the pilot's view of the runway over the nose of the aircraft during landing.

There are many different designs of flaps, with the specific choice depending on the size, speed and complexity of the aircraft on which they are to be used, as well as the era in which the aircraft was designed. Plain flaps, [[slotted flap]]s, and [[Fowler flap]]s are the most common. [[Krueger flap]]s are positioned on the leading edge of the wings and are used on many jet airliners. The Fowler, Fairey-Youngman and Gouge types of flap increase the wing area in addition to changing the camber. The larger lifting surface reduces [[wing loading]], hence further reducing the stalling speed.

Some flaps are fitted elsewhere. Leading-edge flaps form the wing leading edge and when deployed they rotate down to increase the wing camber. The [[de Havilland DH.88 Comet]] racer had flaps running beneath the fuselage and forward of the wing trailing edge. Many of the [[Waco Custom Cabin series]] biplanes have the flaps at mid-[[Chord (aeronautics)|chord]] on the underside of the top wing.