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Aspect ratio (aeronautics) An ASH 31 glider with very high aspect ratio (AR=33.5) and lift-to-drag ratio (L/D=56) In aeronautics, the aspect ratio of a wing is the ratio of its span to its mean chord. It is equal to the square of the wingspan divided by the wing area. Thus, a long, narrow wing has a high aspect ratio, whereas a short, wide wing ...
The Lanchester-Prandtl lifting-line theory[1] is a mathematical model in aerodynamics that predicts lift distribution over a three-dimensional wing from the wing's geometry. [2] The theory was expressed independently [3] by Frederick W. Lanchester in 1907, [4] and by Ludwig Prandtl in 1918–1919 [5] after working with Albert Betz and Max Munk.
The aspect ratio is the width of the airfoil divided by its chord. If the wing is not rectangular, aspect ratio is written AR=b 2 /s, where AR=aspect ratio, b=span, and s=wing area. Also, a greater angle of attack (or tilt) of the wing or spoiler, creates more downforce, which puts more pressure on the rear wheels and creates more drag.
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. [7] (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.)
Wingtip vortices are circular patterns of rotating air left behind a wing as it generates lift. [1]: 5.14 The name is a misnomer because the cores of the vortices are slightly inboard of the wing tips. [2]: 369 Wingtip vortices are sometimes named trailing or lift-induced vortices because they also occur at points other than at the wing tips.
This indicates how, for a given wing area, high aspect ratio wings are beneficial to flight efficiency. With being a function of angle of attack, induced drag increases as the angle of attack increases. [4]: Section 5.17 The above equation can be derived using Prandtl's lifting-line theory.
In two-dimensional flow around a uniform wing of infinite span, the slope of the lift curve is determined primarily by the trailing edge angle. The slope is greatest if the angle is zero; and decreases as the angle increases. [14] [15] For a wing of finite span, the aspect ratio of the wing also significantly influences the slope of the curve ...
The ratio of the length of a nose cone compared to its base diameter is known as the fineness ratio. This is sometimes also called the aspect ratio, though that term is usually applied to wings and tails. Fineness ratio is often applied to the entire vehicle, considering the overall length and diameter.