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Flaps raise the maximum lift coefficient of the aircraft and therefore reduce its stalling speed. [5] They are used during low speed, high angle of attack flight including take-off and descent for landing. Some aircraft are equipped with "flaperons", which are more commonly called "inboard ailerons" [citation needed]. These devices function ...
A spin can occur if an aircraft is stalled and there is an asymmetric yawing moment applied to it. [17] This yawing moment can be aerodynamic (sideslip angle, rudder, adverse yaw from the ailerons), thrust related (p-factor, one engine inoperative on a multi-engine non-centreline thrust aircraft), or from less likely sources such as severe ...
An aileron (French for "little wing" or "fin") is a hinged flight control surface usually forming part of the trailing edge of each wing of a fixed-wing aircraft. [1] Ailerons are used in pairs to control the aircraft in roll (or movement around the aircraft's longitudinal axis), which normally results in a change in flight path due to the ...
divergence where the aerodynamic forces increase the twist of a wing which further increases forces; control reversal where control activation produces an opposite aerodynamic moment that reduces, or in extreme cases reverses, the control effectiveness; and; flutter which is uncontained vibration that can lead to the destruction of an aircraft.
Adverse yaw is a secondary effect of the inclination of the lift vectors on the wing due to its rolling velocity and of the application of the ailerons. [2]: 327 Some pilot training manuals focus mainly on the additional drag caused by the downward-deflected aileron [3] [4] and make only brief [5] or indirect [6] mentions of roll effects.
This feature is sometimes referred to as structural washout, to distinguish it from aerodynamic washout. Wingtip stall is unlikely to occur symmetrically, especially if the aircraft is maneuvering. As an aircraft turns, the wing tip on the inside of the turn is moving more slowly and is most likely to stall.
When a wing generates aerodynamic lift, it results in a region of downwash between the two vortices. [3] [2]: 8.1.1 [4] Three-dimensional lift and the occurrence of wingtip vortices can be approached with the concept of horseshoe vortex and described accurately with the Lanchester–Prandtl theory.
[1] [5] In 2004, the U.S. FAA issued its first Airplane Upset Recovery Training Aid. [6] The second revision of that document was released in 2008 and is available at the FAA's website. [7] New FAA rules are expected to be finalized in 2010 [needs update], requiring specific training for pilots to recover from aircraft upset incidents. [1]