4. Write down the lift curve equation (lift coefficient versus angle of attack) according to the thin airfoil theory. What is the amount of the lift curve slope for a thin airfoil ? NACA 2412 airfoil LEq.(4.57) ut soefficient 0.4 -0.4 Eg. (4,64)- -0.1 Moment coefficient -0.8 - -0.2 -0. • Re-3.1 X 10 O Re -8.9 X 10 -0.4 -8 8 16 24 a, degrees dc = ? da

4. Write down the lift curve equation (lift coefficient versus angle of attack) according to the thin airfoil theory. What is the amount of the lift curve slope for a thin airfoil ? NACA 2412 airfoil LEq.(4.57) ut soefficient 0.4 -0.4 Eg. (4,64)- -0.1 Moment coefficient -0.8 - -0.2 -0. • Re-3.1 X 10 O Re -8.9 X 10 -0.4 -8 8 16 24 a, degrees dc = ? da

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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Consider a rectangular wing with NACA 0009 airfoil section spanning the test section of a wind tunnel, the test section airflow conditions are standard sea level w/a velocity of 116 mi/hr. The wing is at an angle attack of 4° and the wind tunnel force balance measures a lift of 28.43 lbf. What is the area of the wing? R.N = 3.0 X106; C̟ at angle attack of 4° = 0.4 %3D
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