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  2. NACA airfoil - Wikipedia

    en.wikipedia.org/wiki/NACA_airfoil

    TT: the maximum thickness in percent of chord, as in a four-digit NACA airfoil code. For example, the NACA 23112 profile describes an airfoil with design lift coefficient of 0.3 (0.15 × 2), the point of maximum camber located at 15% chord (5 × 3), reflex camber (1), and maximum thickness of 12% of chord length (12).

  3. File:Streamlines around a NACA 0012.svg - Wikipedia

    en.wikipedia.org/wiki/File:Streamlines_around_a...

    English: Potential-flow streamlines around a NACA 0012 airfoil at 11° angle of attack, with upper and lower streamtubes identified. Computed using the Wolfram Demonstrations Project Code Potential Flow over a NACA Four-Digit Airfoil by Richard L. Fearn and beautified in Adobe Illustrator CS3.

  4. 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

  5. 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:

  6. File:Airfoil geometry.svg - Wikipedia

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

    This work has been released into the public domain by its author, F l a n k e r.This applies worldwide. In some countries this may not be legally possible; if so: F l a n k e r grants anyone the right to use this work for any purpose, without any conditions, unless such conditions are required by law.

  7. File:Wing profile nomenclature.svg - Wikipedia

    en.wikipedia.org/wiki/File:Wing_profile...

    The mean camber line (or simply "camber line") is constituted by the midpoints of all airfoil cross-section segments perpendicular to the chord. Different definitions for the thickness Note that the thickness can be defined in several ways (see File:Airfoil thickness definition.svg). The so-called "British convention" is used here.

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  9. Aerodynamic center - Wikipedia

    en.wikipedia.org/wiki/Aerodynamic_center

    The aerodynamic center is the point at which the pitching moment coefficient for the airfoil does not vary with lift coefficient (i.e. angle of attack), making analysis simpler. [ 1 ] d C m d C L = 0 {\displaystyle {dC_{m} \over dC_{L}}=0} where C L {\displaystyle C_{L}} is the aircraft lift coefficient .

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