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quiz-solution6

# quiz-solution6 - μ α-α o l = A 1 sin φ μ sin φ A 3...

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650:460 Aerodynamics Quiz No. 6 - Solution 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

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Quiz No. 6 A rectangular airfoil has an aspect ratio AR = 6 at an angle of attack α = 6 . The wing section is NACA 0012. There are no flaps. Use two non-zero terms in the Fourier expansion for the circulation distribution Γ( φ ) and evaluate the monoplane equation at φ = 45 and φ = 90 . Compute the lift coefficient C L . Solution The monoplane equation with two non-zero terms is
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Unformatted text preview: μ ( α-α o , l ) = A 1 sin φ ( μ + sin φ ) + A 3 sin 3 φ (3 μ + sin φ ) ±or NACA 0012, α o , l = 0 ◦ . The angle of attack is α = 6 ◦ = 0 . 1047 radians. Also μ = ca o 8 s = 2 π c 4 b = π 2 AR = 0 . 2618 2 Quiz No. 6 Applying the monoplane equation at φ = 45 ◦ and 90 ◦ , . 01939 = 0 . 6851 A 1 + 1 . 055 A 3 . 02742 = 1 . 2618 A 1-1 . 785 A 3 and thus A 1 = 0 . 02488 and A 3 = 0 . 00223 Thus, C L = π AR A 1 = 0 . 469 3...
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quiz-solution6 - μ α-α o l = A 1 sin φ μ sin φ A 3...

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