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# solution6 - 650:460 Aerodynamics Homework Assignment No 6...

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Unformatted text preview: 650:460 Aerodynamics Homework Assignment No. 6 Prof. Doyle Knight Tel: 732 445 4464, Email: [email protected] Office hours: Tues and Thur, 4:30 pm - 6:00 pm and by appointment Fall 2009 1 Problem 7.3 When a GA(W)-1 airfoil section is at an angle of attack of 4 ◦ , the lift coefficient is 1.0. Using Eq (7.20), calculate the angle of attack at which a wing whose aspect ratio is 7.5 would have to operate to generate the same lift coefficient. What would the angle of attack have to be to generate this lift coefficient for a wing whose aspect ratio is 6.0 ? Solution The angles of attack are related by α 2 = α 1 + C L π parenleftbigg 1 AR 2- 1 AR 1 parenrightbigg The first wing has AR 1 = ∞ and C L = 1 . 0 at α 1 = 4 ◦ = 0 . 0698 rad. Thus α 2 = 0 . 0698 + 1 . π parenleftbigg 1 7 . 5- 1 ∞ parenrightbigg = 0 . 1123 rad = 6 . 432 ◦ 2 Problem 7.3 The angle of attack required to generate the same lift coefficient for AR 2 = 6 is α 2 = 0 . 0698 + 1 . π parenleftbigg 1 6- 1 ∞ parenrightbigg = 0 . 1229 rad = 7 . 04 ◦ 3 Problem 7.4 Consider a planar wing ( i.e. , no geometric twist) which has a...
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solution6 - 650:460 Aerodynamics Homework Assignment No 6...

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