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  2. Vortex lattice method - Wikipedia

    en.wikipedia.org/wiki/Vortex_lattice_method

    The number of vortices used vary with the required pressure distribution resolution, and with required accuracy in the computed aerodynamic coefficients. A typical number of vortices would be around 100 for an entire aircraft wing; an Aeronautical Research Council report by Falkner published in 1949 mentions the use of an "84-vortex lattice ...

  3. Lift coefficient - Wikipedia

    en.wikipedia.org/wiki/Lift_coefficient

    It is also useful to show the relationship between section lift coefficient and drag coefficient. The section lift coefficient is based on two-dimensional flow over a wing of infinite span and non-varying cross-section so the lift is independent of spanwise effects and is defined in terms of L ′ {\displaystyle L^{\prime }} , the lift force ...

  4. Lift (force) - Wikipedia

    en.wikipedia.org/wiki/Lift_(force)

    Lift is proportional to the density of the air and approximately proportional to the square of the flow speed. Lift also depends on the size of the wing, being generally proportional to the wing's area projected in the lift direction. In calculations it is convenient to quantify lift in terms of a lift coefficient based on these factors.

  5. Lifting-line theory - Wikipedia

    en.wikipedia.org/wiki/Lifting-line_theory

    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 ...

  6. Wing loading - Wikipedia

    en.wikipedia.org/wiki/Wing_loading

    As stalling is due to wing loading and maximum lift coefficient at a given altitude and speed, this limits the turning radius due to maximum load factor. At Mach 0.85 and 0.7 lift coefficient, a wing loading of 50 lb/sq ft (240 kg/m 2 ) can reach a structural limit of 7.33 g up to 15,000 feet (4,600 m) and then decreases to 2.3 g at 40,000 feet ...

  7. Pressure coefficient - Wikipedia

    en.wikipedia.org/wiki/Pressure_coefficient

    The coefficient of lift for a two-dimensional airfoil section with strictly horizontal surfaces can be calculated from the coefficient of pressure distribution by integration, or calculating the area between the lines on the distribution. This expression is not suitable for direct numeric integration using the panel method of lift approximation ...

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