45:
37:
53:
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the wing will create. (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
84:
is the distance between the trailing edge and the point where the chord intersects the leading edge. The point on the leading edge used to define the chord may be the surface point of minimum radius. For a turbine aerofoil the chord may be defined by the line between points where the front and rear
391:
Note that the figure to the right implies that the MAC occurs at a point where leading or trailing edge sweep changes. That is just a coincidence. In general, this is not the case. Any shape other than a simple trapezoid requires evaluation of the above integral.
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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
648:
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360:
855:
233:
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246:
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
380:
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
449:
155:
Many wings are not rectangular, so they have different chords at different positions. Usually, the chord length is greatest where the wing joins the aircraft's
388:(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.
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587:
457:
117:, rather than tapered or swept, then the chord is simply the width of the wing measured in the direction of airflow.) The term
17:
734:
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of the MAC. Therefore, not only the length but also the position of MAC is often important. In particular, the position of
849:
300:
717:
860:
815:
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701:
677:
184:) is used, although it is complex to calculate. The mean aerodynamic chord is used for calculating pitching moments.
198:
264:
880:
885:
451:) and the span (b) of the wing, the chord at any position on the span can be calculated by the formula:
421:
174:
design. To provide a characteristic figure that can be compared among various wing shapes, the
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Flight dynamics principles : a linear systems approach to aircraft stability and control
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797:, Section 1.4 (page 27), Dover Publications Inc., New York, Standard Book Number 486-60586-8
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of a 2-dimensional blade section would touch a flat surface when laid convex-side up.
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https://www.abbottaerospace.com/downloads/nasa-sp-290-turbine-design-and-application/
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404:
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420:"Taper ratio" redirects here. For taper ratio in space elevator construction, see
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104:/rotor blades of an aircraft are all based on aerofoil sections, and the term
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27:
Imaginary straight line joining the leading and trailing edges of an aerofoil
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810:, Chapter 3, (p.103, eighth edition), Pitman Publishing Limited, London
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Standard mean chord (SMC) is defined as wing area divided by wing span:
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Houghton, E. L.; Carpenter, P.W. (2003). Butterworth
Heinmann (ed.).
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643:{\displaystyle \lambda ={\frac {C_{\rm {Tip}}}{C_{\rm {Root}}}}}
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The term is also applied to compressor and turbine aerofoils in
130:
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399:) of a rectangular-planform wing to its chord is known as the
572:{\displaystyle c(y)={\frac {2\,S_{w}}{(1+\lambda )b}}\left.}
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163:) and decreases along the wing toward the wing's tip (the
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830:, Apuntes de la materia, UTN-FRH, Haedo, Buenos Aires
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751:(3rd ed.). Waltham, MA: Butterworth-Heinemann.
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355:{\displaystyle \int _{0}^{\frac {b}{2}}c(y)^{2}dy,}
672:, Section 5.2, Pitman Publishing Limited, London.
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729:The Design Of The Aeroplane, Darrol Stinton 1984,
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793:Abbott, I.H., and Von Doenhoff, A.E. (1959),
779:: CS1 maint: multiple names: authors list (
258:Mean aerodynamic chord (MAC) is defined as:
228:{\displaystyle {\mbox{SMC}}={\frac {S}{b}},}
291:{\displaystyle {\mbox{MAC}}={\frac {2}{S}}}
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369:is the coordinate along the wing span and
68:is an imaginary straight line joining the
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48:Chord line of a turbine aerofoil section.
856:Finding the Mean Aerodynamic Chord (MAC)
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40:Aerofoil nomenclature showing chord line
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152:engines for aircraft propulsion.
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373:is the chord at the coordinate
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395:The ratio of the length (or
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408:low airspeeds. This is why
167:). Most jet aircraft use a
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844:Aerodynamics for Students
412:have long slender wings.
444:{\displaystyle \lambda }
826:Ruggeri, M.C., (2009),
795:Theory of Wing Sections
806:Kermode, A.C. (1972),
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56:Chords on a swept-wing
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18:Mean aerodynamic chord
881:Aircraft aerodynamics
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32:Wing chord (biology)
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159:(called the
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110:chord length
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82:chord length
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70:leading edge
65:
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876:Aeronautics
138:gas turbine
62:aeronautics
870:Categories
653:References
172:swept wing
161:root chord
123:wing flaps
30:See also:
775:cite book
767:818173505
592:λ
537:λ
534:−
525:−
505:λ
439:λ
306:∫
165:tip chord
146:turboprop
102:propeller
668:(1975),
157:fuselage
150:turbofan
142:turbojet
127:ailerons
115:planform
78:aerofoil
720:, p.66
410:gliders
169:tapered
80:. The
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737:, p.26
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676:
582:where
365:where
238:where
131:rudder
76:of an
64:, the
148:, or
119:chord
106:chord
66:chord
812:ISBN
781:link
763:OCLC
753:ISBN
731:ISBN
708:p.18
698:ISBN
674:ISBN
397:span
129:and
100:and
90:wing
88:The
72:and
271:MAC
205:SMC
182:MAC
108:or
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