Camber (Aerodynamics) - Wikipedia, The Free Encyclopedia

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Camber (aerodynamics)

From Wikipedia, the free encyclopedia

In aeronautics and aeronautical engineering, camber is the asymmetry between the top and the

bottom surfaces of an aerofoil. An aerofoil that is not cambered is called asymmetric aerofoil. The

benefits ofcamber, in contrast to symmetric aerofoils, were discovered and first utilized by Sir

George Cayley in the early 19th century.[1]

Contents

1 Overview

2 Definition

2.1 Example An aerofoil with reflexed camber line

3 References

4 References

5 See also

Overview

Camber is usually designed into an aerofoil to increase the maximum lift coefficient. This minimises the stalling speed of aircraft using the aerofoil. Aircraft

with wings based on cambered aerofoils usually have lower stalling speeds than similar aircraft with wings based on symmetric aerofoils.

An aircraft designer may also reduce the camber of the outboard section of the wings to increase the critical angle of attack (stall angle) at the wing tips.

When the wing approaches the stall angle this will ensure that the wing root stalls before the tip, giving the aircraft resistance to spinning and maintaining

aileron effectiveness close to the stall.[citation needed]

Some recent designs use negative camber. One such design is called the supercritical aerofoil. It is used for near-supersonic flight, and produces a higher

lift to drag ratio at near supersonic flight than traditional aerofoils. Supercritical aerofoils employ a flattened upper surface, highly cambered (curved) aftsection, and greater leading edge radius as compared to traditional aerofoil shapes. These changes delay the onset of wave drag.
http://en.wikipedia.org/wiki/File:Aerodynamic_camber.jpghttp://en.wikipedia.org/wiki/Wave_draghttp://en.wikipedia.org/wiki/Supersonic_flighthttp://en.wikipedia.org/wiki/Supercritical_aerofoilhttp://en.wikipedia.org/wiki/Wikipedia:Citation_neededhttp://en.wikipedia.org/wiki/Spin_(flight)http://en.wikipedia.org/wiki/Stall_(flight)http://en.wikipedia.org/wiki/Lift_coefficienthttp://en.wikipedia.org/wiki/Aerofoilhttp://en.wikipedia.org/wiki/Sir_George_Cayleyhttp://en.wikipedia.org/wiki/Aerofoilhttp://en.wikipedia.org/wiki/Aeronautical_engineeringhttp://en.wikipedia.org/wiki/Aeronautics


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An aerofoil with reflex camber.

Definition

The camber of an aerofoil can be defined by a camber line, which is the curve that is halfway between the upper and lower surfaces of the aerofoil. Call

this functionZ(x). To fully define an aerofoil we also need a thickness function T(x), which describes the thickness of the aerofoil at any given point.

Then, the upper and lower surfaces can be defined as follows:

Example An aerofoil with reflexed camber line

An aerofoil where the camber line curves back up near the trailing edge is called a

reflexed camber aerofoil. Such an aerofoil is useful in certain situations, such as withtailless aircraft, because the moment about the aerodynamic center of the aerofoil can be

0. A camber line for such an aerofoil can be defined as follows (note that the lines over

the variables indicates that they have been nondimensionalized by dividing through

by the chord):

An aerofoil with a reflexed camber line is shown at right. The thickness distribution for a

NACA 4-series aerofoil was used, with a 12% thickness ratio. The equation for thisthickness distribution is:

Where tis the thickness ratio.
http://en.wikipedia.org/wiki/NACA_airfoilhttp://en.wikipedia.org/wiki/Nondimensionalizationhttp://en.wikipedia.org/wiki/Aerodynamic_centerhttp://en.wikipedia.org/wiki/Moment_(physics)http://en.wikipedia.org/wiki/Tailless_aircrafthttp://en.wikipedia.org/wiki/File:Reflex_camber_line.jpg


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References

1. ^ "U.S Centennial of Flight Commission." (http://www.centennialofflight.gov/essay/Prehistory/Cayley/PH2.htm). Retrieved 2008-09-10.

"Experiments that he began to carry out in 1804 allowed him to learn more about aerodynamics and wing structures using a whirling arm device.

Cayley observed that birds soared long distances by simply twisting their arched wing surfaces and deduced that fixed-wing machines would fly if

the wings were cambered. This was the first scientific testing of aerofoils as the part of the aircraft that is designed to produce lift."

References

Desktop Aerodynamics Digital Textbook. Retrieved 9/7/08. [1] (http://www.desktopaero.com/appliedaero/airfoils1/airfoilgeometry.html)

Theory of Wing Sections, Ira H.Abbott and Albert E.Von Doenhoff (Dover Publications-1959) ISBN 0-486-60586-8

See also

ChordNACA airfoil

Drag_(physics)#Drag_in_aerodynamics

Zero lift axis

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