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The NACA 4412 airfoil has a mean camber line given by C 0.25 [0.8% - (2)], for 00.4 0.111 [0.2+0.8% (2)], for 0.4
The NACA 4412 airfoil has a mean camber line given by C 0.25 [0.8% - (2)], for 00.4 0.111 [0.2+0.8% (2)], for 0.4
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Fundamentals of Aerodynamics
Authors: J. Anderson
2nd Edition
978-0071254083, 1259129918, 71254080, 70016798, 9781259129919, 978-0070016798
