Engineering:Thickness-to-chord ratio

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Short description: Ratio in aeronautics
a=chord, b=thickness, thickness-to-chord ratio = b/a
The F-104 wing has a very low thickness-to-chord ratio of 3.36%

In aeronautics, the thickness-to-chord ratio, sometimes simply chord ratio or thickness ratio, compares the maximum vertical thickness of a wing to its chord. It is a key measure of the performance of a wing planform when it is operating at transonic speeds.

At speeds approaching the speed of sound, the effects of Bernoulli's principle over curves on the wing and fuselage can accelerate the local flow to supersonic speeds. This creates a shock wave that produces a powerful form of drag known as wave drag, and gives rise to the concept of the sound barrier. The speed at which these shocks first form, critical mach, is a function of the amount of curvature. In order to reduce wave drag, wings should have the minimum curvature possible while still generating the required amount of lift. So, the main reason for decreasing the blade section thickness to chord ratio is to delay the compressibility effect related to higher Mach numbers, delaying the onset of a shock wave formation.

The natural outcome of this requirement is a wing design that is thin and wide, which has a low thickness-to-chord ratio. At lower speeds, undesirable parasitic drag is largely a function of the total surface area, which suggests using a wing with minimum chord, leading to the high aspect ratios seen on light aircraft and regional airliners. Such designs naturally have high thickness-to-chord ratios. Designing an aircraft that operates across a wide range of speeds, like a modern airliner, requires these competing needs to be carefully balanced for every aircraft design.

Swept wings are a practical outcome of the desire to have a low thickness-to-chord ratio at high speeds and a lower one at lower speeds during takeoff and landing. The sweep stretches the chord as seen by the airflow, while still keeping the wetted area of the wing to a minimum. For practical reasons, wings tend to be thickest at the root, where they meet the fuselage. For this reason, it is common for wings to taper their chord towards the tips, keeping the thickness-to-chord ratio close to constant, this also reduces induced drag at lower speeds. The crescent wing is another solution to the design to keep a relatively constant thickness-to-chord ratio.

Airliners[1] Area
(m²)
Span
(m)
Aspect
Ratio
Taper
Ratio
Average
(t/c) %
1/4 Chord
Sweep (°)"
ERJ 145 51.18 20.04 7.85 0.231 11.00 22.73
CRJ100 54.54 20.52 7.72 0.288 10.83 24.75
Avro RJ 77.30 26.21 8.89 0.356 12.98 15.00
737 Original/Classic 91.04 28.35 8.83 0.266 12.89 25.00
DC-9 92.97 28.47 8.72 0.206 11.60 24.00
Boeing 717 92.97 28.40 8.68 0.196 11.60 24.50
Fokker 100/70 93.50 28.08 8.43 0.235 10.28 17.45
MD-80/90 112.30 32.87 9.62 0.195 11.00 24.50
A320 122.40 33.91 9.39 0.240 11.92[2] 25.00
737 NG 124.60 34.30 9.44 0.278 25.00
Boeing 727 157.90 32.92 6.86 0.309 11.00 32.00
Boeing 757 185.25 38.05 7.82 0.243 25.00
A310 219.00 43.89 8.80 0.283 11.80 28.00
A300 260.00 44.84 7.73 0.300 10.50 28.00
DC-8 271.90 45.23 7.52 0.181 11.00 30.00
Boeing 767 283.30 47.57 7.99 0.207 11.50 31.50
Boeing 707 283.40 44.42 6.96 0.259 10.00 35.00
MD-11 338.90 51.77 7.91 0.239 9.35 35.00
A330/A340-200/300 363.10 58.00 9.26 0.251 11.80[2] 29.70
DC-10 367.70 50.40 6.91 0.220 11.00 35.00
Boeing 777 427.80 60.90 8.67 0.149 31.60
A340-500/600 437.30 61.20 8.56 0.220 31.10
747 Classic 511.00 59.64 6.96 0.284 9.40 37.50
747-400 525.00 62.30 7.39 0.275 9.40 37.50
MD-12 543.00 64.92 7.76 0.215 35.00
A3XX 817.00 79.80 7.79 0.213 30.00


References

Further reading