EBK FUNDAMENTALS OF AERODYNAMICS
EBK FUNDAMENTALS OF AERODYNAMICS
6th Edition
ISBN: 9781259681486
Author: Anderson
Publisher: MCGRAW HILL BOOK COMPANY
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Chapter 4, Problem 4.6P

The NACA 4412 airfoil has a mean camber line given by z c = { 0.25 [ 0.8 x c ( x c ) 2 ] for 0 x c 0.4 0.111 [ 0.2 + 0.8 x c ( x c ) 2 ] for 0.4 x c 1

Using thin airfoil theory, calculate

(a) α L = 0

(b) c l when α = 3 °

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