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Adaptive Compliant Trailing Edge (ACTE) is a research project on shape-changing flaps for aircraft wings, intended to reduce the aircraft's fuel costs and reduce noise during take-off and landing. It is a join effort by NASA and the U.S. Air Force Research Laboratory [ 1 ] and first airborne tests have been conducted in late 2014.
Trailing edge flaps extended on the right on a typical airliner (an Airbus A310-300). Leading edge slats are also extended, on the left. A flap is a high-lift device used to reduce the stalling speed of an aircraft wing at a given weight. Flaps are usually mounted on the wing trailing edges of a fixed-wing aircraft. Flaps are used to reduce the ...
The position of the leading-edge slats on an airliner (Airbus A310-300). In this picture, the slats are drooped. 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.
To test the AAW theory, NASA and the USAF agreed to fund development of a single demonstrator, based on the F/A-18. Work started by taking an existing F/A-18 airframe modified with a preproduction wing, and added an outboard leading edge flap drive system and an updated flight control computer.
An adaptive compliant wing designed by FlexSys Inc. features a variable-camber trailing edge which can be deflected up to ±10°, thus acting like a flap-equipped wing, but without the individual segments and gaps typical in a flap system. The wing itself can be twisted up to 1° per foot of span.
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 Gurney flap (or wickerbill) is a small tab projecting from the trailing edge of a wing. Typically it is set at a right angle to the pressure-side surface of the airfoil [2] and projects 1% to 2% of the wing chord. [3] This trailing edge device can improve the performance of a simple airfoil to nearly the same level as a complex high ...
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 ...