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4.6 The NACA 4412 airfoil has a mean camber line given by 0.25 25 [0.8 - (3) ] for 0 x 0.4 0.111 1
4.6 The NACA 4412 airfoil has a mean camber line given by 0.25 25 [0.8 - (3) ] for 0 x 0.4 0.111 1 [0.2 + 0.8 - ( 2 ) ] for 0.41 C Using thin airfoil theory, calculate (a) -0 (b) c, when = 3 (c) Cc14 and (d) xcp/c when =3.
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Fundamentals of Ethics for Scientists and Engineers
Authors: Edmund G. Seebauer, Robert L. Barry
1st Edition
9780195698480, 195134885, 195698487, 978-0195134889
