# Chord (aeronautics)

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Chord of an aerofoil section.
Chords on a swept-wing

In aeronautics, a chord is the imaginary straight line joining the leading and trailing edges of an aerofoil. The chord length is the distance between the trailing edge and the point on the leading edge where the chord intersects the leading edge.[1][2]

The point on the leading edge that is used to define the chord can be defined as either the surface point of minimum radius,[2] or the surface point that will yield maximum chord length[citation needed].

The wing, horizontal stabilizer, vertical stabilizer and propeller of an aircraft are all based on aerofoil sections, and the term chord or chord length is also used to describe their width. The chord of a wing, stabilizer and propeller is determined by measuring the distance between leading and trailing edges in the direction of the airflow. (If a wing has a rectangular planform, rather than tapered or swept, then the chord is simply the width of the wing measured in the direction of airflow.) The term chord is also applied to the width of wing flaps, ailerons and rudder on an aircraft.

The term is also applied to aerofoils in gas turbine engines such as turbojet, turboprop, or turbofan engines for aircraft propulsion.

Most wings are not rectangular so they have a different chord at different positions along their span. To give a characteristic figure that 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.

## Standard mean chord

Standard mean chord (SMC) is defined as wing area divided by wing span:[3][citation needed]

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

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:[4]

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

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 on and a moment around the aerodynamic center of the MAC. Therefore, not only the length but also the position of MAC is often important. In particular, the position of center of gravity (CG) of an aircraft is usually measured relative to the MAC, as the percentage of the distance from the leading edge of MAC to CG 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 rectangular-planform wing to its chord is known as the aspect ratio, an important indicator of the lift-induced drag the wing will create.[5] (For wings with planforms that are not rectangular, the aspect ratio is calculated as the square of the span divided by the wing planform area.) Wings with higher aspect ratios will have less induced drag than wings with lower aspect ratios. Induced drag is most significant at low airspeeds. This is why gliders have long slender wings.

## Tapered wing

Knowing the area (Sw), taper ratio (${\displaystyle \lambda }$) and the span (b) of the wing, the chord at any position on the span can be calculated by the formula:[6]

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

where

${\displaystyle \lambda ={\frac {C_{\rm {Tip}}}{C_{\rm {Root}}}}}$

NOTE: This formula only works if y=0 is the port wingtip and y=b is the starboard wingtip. Typically, y=0 represents the midspan location.

Note 2: The formula as presented does not work regardless of whether one uses y = 0 -> port tip or not, and the note is not consistent with the use of the absolute value of y in the formula. The formula should read

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

## References

1. ^ L. J. Clancy (1975), Aerodynamics, Section 5.2, Pitman Publishing Limited, London. ISBN 0-273-01120-0
2. ^ a b Houghton, E. L.; Carpenter, P.W. (2003). Butterworth Heinmann, ed. Aerodynamics for Engineering Students (5th ed.). ISBN 0-7506-5111-3. p.18
3. ^ V., Cook, M. (2013). Flight dynamics principles : a linear systems approach to aircraft stability and control (3rd ed.). Waltham, MA: Butterworth-Heinemann. ISBN 9780080982427. OCLC 818173505.
4. ^ Abbott, I.H., and Von Doenhoff, A.E. (1959), Theory of Wing Sections, Section 1.4 (page 27), Dover Publications Inc., New York, Standard Book Number 486-60586-8
5. ^ Kermode, A.C. (1972), Mechanics of Flight, Chapter 3, (p.103, eighth edition), Pitman Publishing Limited, London ISBN 0-273-31623-0
6. ^ Ruggeri, M.C., (2009), Aerodinámica Teórica, Apuntes de la materia, UTN-FRH, Haedo, Buenos Aires