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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 commonly achieved by designing the wing with a slight twist, reducing the angle of incidence from root to tip, and therefore causing a lower angle of attack at the tips than at the roots. This feature is sometimes referred to as geometrical washout, to distinguish it from aerodynamic washout.
Wing morphing is a modern-day extension of wing warping in which the aerodynamic shape of the wing is modified under computer control. Research into this field is mainly conducted by NASA such as with the Mission Adaptive Wing (MAW) trialed from 1985 on the General Dynamics–Boeing AFTI/F-111A Aardvark.
Spoiler controls can be used for roll control (outboard or mid-span spoilers) or descent control (inboard spoilers). Some aircraft use spoilers in combination with or in lieu of ailerons for roll control, primarily to reduce adverse yaw when rudder input is limited by higher speeds.
A tumblewing or "tumble wing" or "tumbling wing" is a glider or kite wing design which rotates about an axis transverse to the apparent wind, not necessarily horizontal. Tumble wings are frequently employed in wind turbines (such as the Savonius design ), and are also used in some types of confetti .
A spin is more complex, involving intentionally stalling a single wing, causing the plane to descend spiraling around its yaw axis in a corkscrew motion. A hammerhead (also known as a stall turn ) is performed by pulling the aircraft up until it is pointing straight up (much like the beginning of a loop), but the pilot continues to fly straight ...
A Boeing 737 uses an adjustable stabilizer, moved by a jackscrew, to provide the required pitch trim forces. Generic stabilizer illustrated. A horizontal stabilizer is used to maintain the aircraft in longitudinal balance, or trim: [3] it exerts a vertical force at a distance so the summation of pitch moments about the center of gravity is zero. [4]
A wing of infinite span and uniform airfoil segment (or a 2D wing) would experience no induced drag. [11] The drag characteristics of a wing with infinite span can be simulated using an airfoil segment the width of a wind tunnel. [12] An increase in wingspan or a solution with a similar effect is one way to reduce induced drag.