Answered: Using thin airfoil theory, calculate cl…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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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 c_lwhen α = 2.4°. (Round the final answer to three decimal places. You must provide an answer before moving on to the next part.)

c_l =

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