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  2. NACA airfoil - Wikipedia

    en.wikipedia.org/wiki/NACA_airfoil

    Four- and five-digit series airfoils can be modified with a two-digit code preceded by a hyphen in the following sequence: One digit describing the roundness of the leading edge, with 0 being sharp, 6 being the same as the original airfoil, and larger values indicating a more rounded leading edge.

  3. File:Examples of Airfoils.svg - Wikipedia

    en.wikipedia.org/wiki/File:Examples_of_Airfoils.svg

    English: Selected airfoils in nature and various vehicles, with their approximate chord length indicated. Sources for the shapes of the airfoils: Low-speed ULM wing: drawn over own photo of low-cost, low-speed ultralight; Propeller blade: drawn over own photo of a sliced WW2-era bomber propeller

  4. Airfoil - Wikipedia

    en.wikipedia.org/wiki/Airfoil

    For example, an airfoil of the NACA 4-digit series such as the NACA 2415 (to be read as 2 – 4 – 15) describes an airfoil with a camber of 0.02 chord located at 0.40 chord, with 0.15 chord of maximum thickness. Finally, important concepts used to describe the airfoil's behaviour when moving through a fluid are:

  5. Aerodynamic center - Wikipedia

    en.wikipedia.org/wiki/Aerodynamic_center

    For symmetrical airfoils =, so the aerodynamic center is at 25% of chord measured from the leading edge. But for cambered airfoils the aerodynamic center can be slightly less than 25% of the chord from the leading edge, which depends on the slope of the moment coefficient, . These results obtained are calculated using the thin airfoil theory so ...

  6. Supercritical airfoil - Wikipedia

    en.wikipedia.org/wiki/Supercritical_airfoil

    Supercritical airfoils feature four main benefits: they have a higher drag-divergence Mach number, [21] they develop shock waves farther aft than traditional airfoils, [22] they greatly reduce shock-induced boundary layer separation, and their geometry allows more efficient wing design (e.g., a thicker wing and/or reduced wing sweep, each of which may allow a lighter wing).

  7. Kline–Fogleman airfoil - Wikipedia

    en.wikipedia.org/wiki/Kline–Fogleman_airfoil

    Further development resulted in two patents and a family of airfoils known as the KF airfoil and KFm airfoils (for Kline–Fogleman modified). The two patents, US Patent # 3,706,430 and US Patent # 4,046,338, refer to the introduction of a step on either the bottom (KFm1) or the top (KFm2) of an airfoil , or on both the top and bottom (KFm4).

  8. Lift coefficient - Wikipedia

    en.wikipedia.org/wiki/Lift_coefficient

    For a thin airfoil of any shape the lift slope is π 2 /90 ≃ 0.11 per degree. At higher angles a maximum point is reached, after which the lift coefficient reduces. The angle at which maximum lift coefficient occurs is the stall angle of the airfoil, which is approximately 10 to 15 degrees on a typical airfoil.

  9. Gurney flap - Wikipedia

    en.wikipedia.org/wiki/Gurney_flap

    A Gurney flap shown on the underside of a Newman airfoil [1]. The Gurney flap (or wickerbill) is a small tab projecting from the trailing edge of a wing. Typically it is set at a right angle to the pressure-side surface of the airfoil [2] and projects 1% to 2% of the wing chord. [3]