Chord (aircraft).html

This article does not cite any references or sources.
Please help improve this article by adding citations to reliable sources. Unverifiable material may be challenged and removed. (September 2008)

Cross section of an airfoil showing chord

The various chords on a wing of an aircraft.

In reference to aircraft, chord refers to the distance between the leading edge and trailing edge of a wing, horizontal stabilizer or vertical stabilizer, measured in the direction of the normal airflow. The term is also used to describe the width of the blades of a propeller, the width of wing flaps, ailerons and rudder on an aircraft.

Most wings do not have a rectangular planform so they have a different chord at different positions along their span. To give a characteristic figure which can be compared among various wing shapes, the mean aerodynamic chord, or MAC, is used. The MAC is somewhat more complex to calculate, because most wings vary in chord over the span, growing narrower towards the outer tips. This means that more lift is generated on the wider inner portions, and the MAC moves the point to measure the chord to take this into account. (If a wing were rectangular, rather than tapered or swept, then the chord would simply be the width of the wing in the direction of airflow.)

1 Standard mean chord
2 Mean aerodynamic chord
3 Tapered wing
4 References
5 See also
6 External links

Standard mean chord

Standard mean chord (SMC) is defined as wing area divided by wing span:^{citation needed}

$\mbox{SMC} = \frac{S}{b}$ ,

where S is the wing area and b is the span of the wing. Thus, the SMC is the chord of a rectangular wing with the same area and span as those of the given wing. This is a purely geometric figure and is rarely used in aerodynamics.

Mean aerodynamic chord

Mean aerodynamic chord (MAC) is defined as:^{citation needed}

$\mbox{MAC} = \frac{2}{S}$ $\int_{0}^{\frac{b}{2}}c^2(y) dy$ ,

where y is the coordinate along the wing span and c(y) is the chord at the coordinate y. Other terms are as for SMC.

Physically, MAC is the chord of a rectangular wing, which has the same area, aerodynamic force and position of the center of pressure at a given angle of attack as the given wing has. Simply stated, MAC is the width of an equivalent rectangular wing in given conditions. Therefore, not only the measure but also the position of MAC is often important. In particular, the position of center of mass (CoM) of an aircraft is usually measured relative to the MAC, as the percentage of the distance from the leading edge of MAC to CoM with respect to MAC itself.

Note that the figure to the right implies that the MAC occurs at a point where leading or trailing edge sweep changes. In general, this is not the case. Any shape other than a simple trapezoid requires evaluation of the above integral.

The ratio of the length (or span) of a wing to its chord is known as the aspect ratio, an important indicator of the lift-induced drag the wing will create. In general, planes with higher aspect ratios — long, skinny wings — will have less induced drag, which dominates at low airspeeds. This is why gliders have long wings.

Tapered wing

Knowing the area (S_w), taper ratio ( $λ$ ) and the span (b) of the wing, and whether the wing has sweep or not, the chord at any position on the span can be calculated by the formula:^{citation needed}

$c(y)=\frac{2\,S_w}{(1+\lambda)b}\left[1-\frac{2(1-\lambda)}{b}y\right]$

Chord (aircraft).html

Contents

Standard mean chord

Mean aerodynamic chord

Tapered wing

References

See also

External links