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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.
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
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:
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TT: the usual two-digit maximum camber in percent of chord; Accordingly, the given example “77887” is nonsensical. You simply cannot have a an “8” in the middle position: it _must_ be either “0” or “1”. An 87%-of-chord thickness is also highly dubious: _none_ of the canonical NACA profiles (10 5-digit and 87 4-digit) go beyond 25%.
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Note: Most subscribers have some, but not all, of the puzzles that correspond to the following set of solutions for their local newspaper. CROSSWORDS
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 ...