Elements Of Electromagnetics
7th Edition
ISBN: 9780190698614
Author: Sadiku, Matthew N. O.
Publisher: Oxford University Press
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Problem 04.006 DEPENDENT MULTI-PART PROBLEM - ASSIGN ALL PARTS
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The NACA 4412 airfoil has a mean camber line given by
zc=⎧⎩⎨⎪⎪0.25[0.8xc− (xc)2]0.111[0.2+0.8xc− (xc)2]for 0≤xc≤0.4for 0.4≤xc≤1⎫⎭⎬⎪⎪zc={0.25[0.8xc− (xc)2]for 0≤xc≤0.40.111[0.2+0.8xc− (xc)2]for 0.4≤xc≤1}
Problem 04.006.b - Lift coefficient for a NACA 4412 airfoil
Using thin airfoil theory, calculate cl when α = 2.4°. (Round the final answer to three decimal places. You must provide an answer before moving on to the next part.)
cl =
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