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Wing twist is an aerodynamic feature added to aircraft wings to adjust lift distribution along the wing.. Often, the purpose of lift redistribution is to ensure that the wing tip is the last part of the wing surface to stall, for example when executing a roll or steep climb; it involves twisting the wingtip a small amount downwards in relation to the rest of the wing.
Washout is a characteristic of aircraft wing design which deliberately changes the lift distribution across the span of an aircraft’s wing. The wing is designed so that the angle of incidence is greater at the wing roots and decreases across the span, becoming lowest at the wing tip .
The original designs were in the form of a fixed slot near the leading edge of the wing, a design that was used on a number of STOL aircraft. During World War II, German aircraft commonly fitted a more advanced version of the slat that reduced drag by being pushed back flush against the leading edge of the wing by air pressure , popping out ...
The non-planar wing tip is often swept back like a raked wingtip and may also be combined with a winglet. A winglet is also a special case of a non-planar wingtip. [citation needed] Aircraft designers employed mostly planar wing designs with simple dihedral after World War II, prior to the introduction of winglets.
Mounted above this slot was a small secondary airfoil called an "augmentor", intended to direct the discharged airflow over the wing. With this arrangement, it was found that the aircraft remained controllable at airspeeds as low as 34.76 kn (64.38 km/h; 40.00 mph). The US Navy considered developing the Jetwing for use on short aircraft carriers.
Angle of incidence of an airplane wing on an airplane. On fixed-wing aircraft, the angle of incidence (sometimes referred to as the mounting angle [1] or setting angle) is the angle between the chord line of the wing where the wing is mounted to the fuselage, and a reference axis along the fuselage (often the direction of minimum drag, or where applicable, the longitudinal axis).
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The airspeed at which the aircraft stalls varies with the weight of the aircraft, the load factor, the center of gravity of the aircraft and other factors. However, the aircraft normally stalls at the same critical angle of attack, unless icing conditions prevail. The critical or stalling angle of attack is typically around 15° - 18° for many ...