4.6 The NACA 4412 airfoil has a mean camber line given by [0.25 [0.8-(+)] 11 [0.2...

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4.6 The NACA 4412 airfoil has a mean camber line given by [0.25 [0.8-(+)] 11 [0.2 x 0.111 0.2+0.8- Using thin airfoil theory, calculate (a) -0 (b) c when = 3 - X for 0 () ] 0.4 (*)*] for 0.41 4.6 The NACA 4412 airfoil has a mean camber line given by [0.25 [0.8-(+)] 11 [0.2 x 0.111 0.2+0.8- Using thin airfoil theory, calculate (a) -0 (b) c when = 3 - X for 0 () ] 0.4 (*)*] for 0.41