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# solution5 - 650:460 Aerodynamics Homework Assignment No 5...

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650:460 Aerodynamics Homework Assignment No. 5 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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Problem 7.1 Consider an airplane that weighs 14,700 N and cruises in level flight at 300 km/hr at an altitude of 3 km. The wing has a surface area of 17 m 2 and an aspect ratio of 6.2. Assume that the lift coefficient is a linear function of the angle of attack and that α o , l = - 1 . 2 . If the load distribution is elliptic, calculate the value of the circulation in the plane of symmetry Γ o , the downwash velocity w ( y 1 ), the induced drag coefficient C D v , the geometric angle of attack α and the effective angle of attack α e . Solution The velocity of the airplane is U = 83 . 33 m/s. At 3 km altitude, the density is ρ = 0 . 9092 kg/m 3 . Thus, the dynamic pressure is q = 1 2 ρ U 2 = 3156 . 9 Pa 2
Problem 7.1 Since the aspect ratio AR = 6 . 2, b = AR · S = 10 . 27 m The lift coefficient is C L = L q S = π b Γ o 2 U S Thus, Γ o = 2 U L q π b = 24 .

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