EBK FUNDAMENTALS OF AERODYNAMICS
EBK FUNDAMENTALS OF AERODYNAMICS
6th Edition
ISBN: 9781259681486
Author: Anderson
Publisher: MCGRAW HILL BOOK COMPANY
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Chapter 5, Problem 5.3P

The measured lift slope for the NACA 23012 airfoil is 0.1080 degree 1 , and α L = 0 = 1.3 ° . Consider a finite wing using this airfoil, with A R = 8 and taper ratio = 0.8 . Assume that δ = τ . Calculate the lift and induced drag coefficients for this wing at a geometric angle of attack = 7 ° .

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