![]() ![]() The NACA five-digit series describes more complex airfoil shapes. \dfrac \left(p - x\right), & p \leq x \leq 1. The formula for the shape of a NACA 00xx foil, with "xx" being replaced by the percentage of thickness to chord, is Equation for a symmetrical 4-digit NACA airfoil The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long. ![]() The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. įor example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord.
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