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Mean aerodynamic chord (MAC) is defined as: [6] = (), where y is the coordinate along the wing span and c is the chord at the coordinate y.Other terms are as for SMC. The MAC is a two-dimensional representation of the whole wing. The pressure distribution over the entire wing can be reduced to a single lift force
The triple-slotted trailing edge flaps are well displayed and the Krueger flaps on the leading edge also are visible. In aircraft design and aerospace engineering, a high-lift device is a component or mechanism on an aircraft's wing that increases the amount of lift produced by the wing. The device may be a fixed component, or a movable ...
The leading edge of the flap is mounted on a track, while a point at mid chord on the flap is connected via an arm to a pivot just above the track. When the flap's leading edge moves aft along the track, the triangle formed by the track, the shaft and the surface of the flap (fixed at the pivot) gets narrower and deeper, forcing the flap down. [20]
A fixed leading-edge slot can increase the maximum lift coefficient of an airfoil section by 40%. In conjunction with a slat, the increase in maximum lift coefficient can be 50% or even 60%. [2] [5] Unlike trailing edge flaps, leading-edge slots do not increase the lift coefficient at zero angle of attack since they do not alter the camber. [6]
The angle between the upper and lower surfaces at the trailing edge is called the trailing edge angle. If the trailing edge angle is zero it is described as a cusped trailing edge. [5] In two-dimensional flow around a uniform wing of infinite span, the slope of the lift curve is determined primarily by the trailing edge angle. The slope is ...
Note also the extended trailing-edge flaps. Slats on the leading edge of an Airbus A318 of Air France Automatic slats of a Messerschmitt Bf 109 The wing of a landing Airbus A319-100. The slats at the leading edge and the flaps at the trailing edge are extended. The Fieseler Fi 156 Storch had permanently extended slots on its leading edges ...
The Kutta–Joukowski theorem is a fundamental theorem in aerodynamics used for the calculation of lift of an airfoil (and any two-dimensional body including circular cylinders) translating in a uniform fluid at a constant speed so large that the flow seen in the body-fixed frame is steady and unseparated.
The leading edge is the part of the wing that first contacts the air; [1] [2] alternatively it is the foremost edge of an airfoil section. [3] The first is an aerodynamic definition, the second a structural one.