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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
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).
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:
XFOIL is an interactive program for the design and analysis of subsonic isolated airfoils.Given the coordinates specifying the shape of a 2D airfoil, Reynolds and Mach numbers, XFOIL can calculate the pressure distribution on the airfoil and hence lift and drag characteristics.
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.
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