An airplane weighs \(320,000 \mathrm{lb}\), has a wing area of \(2800 \mathrm{ft}^{2}\), and has a wing length of \(140 \mathrm{ft}\). The atmospheric pressure and temperature are \(14.67 \mathrm{psia}\) and \(60^{\circ} \mathrm{F}\), respectively. The airplane is moving along a runway at \(200 \mathrm{mph}\), and the wing has the lift and drag coefficients given in Fig. 9.39. Find the lift and drag on the airplane wings for an angle of attack of \(10^{\circ}\).

Fig. 9.39

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1.4 1.2 =7 1.0 CL 0.8 0.6 0.4 0.2 0 -0.2 -0.4 -10 0 a, degrees 10 (a) -=3 4 1 20 20 0.03 CD 0.02 0.01 = 1 s=3 = 7 -10 0 10 20 20 a, degrees (b)