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Question: 18 c172 16 14 12 12 10 10 08 08...

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1.8 C1.72 1.6 1.4 1.2 1.2 1.0 1.0 0.8 0.8 0.6 0.6 Conventional section (NACA 23015) Laminar-flow section (NACA 662215) 0.4 0.4 0.2 0.2 0 0 0 8 12 16 20 0 8 12 16 2 Angle of attack, α (deg) Angle of attack, α (deg) (a) Lift coefficient vs. angle of attack 0.020 0.020 0.016 0.016 0.012 0.012 0.008 0.008 Conventional section (NACA 23015) Laminar-flow section (NACA 662-215) 0.004 0 0 0 0 8 12 16 20 0 4 8 12 16 20 Angle of attack, (deg) Angle of attack, α (deg) (b) Drag coefficient vs. angle of attack Fig.9.17 Lift and drag coefficients versus angle of attack for two airfoil sections of 15 percent thickness ratio at Re 9x 1o. (Data from Abbott and von Doenhoff [21].)A small airplane weighs 900 kg and has a wing with planform area 12 m2 (a) If the wing section is given by a NACA 23015 profile, use figure 9.17 from the textbook to find the angle of attack required for steady flight at 55m/s. (b) Calculate the power required for steady cruise. (c) Suppose the angle of attack is suddenly increased to the value yielding maximum lift. What is the vertical acceleration?

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