1.36. 1.37. 1.38. Write a computer program that uses the numerical lifting-line method presented in Sec. 1.9 to predict the lift and induced drag for a tapered wing with linear geometric and aerodynamic twist. Test your program by comparing results with those obtained in problems 1.27, 1.28, 1.32, and 1.33. Use the program from problem 1.36 to compute the lift at a 10-degree angle of attack for a rectangular wing with a thin symmetric airfoil section and an aspect ratio of 6. The root chord is 5.5 ft. Use V = 176 ft/sec at standard sea level. Use the computer program that was written for problem 1.36 to compute the lift at a 10-degree angle of attack for a tapered wing having aspect ratio 4.0, taper ratio 0.5, and a thin symmetric airfoil section. The wing quarter chord is swept such that there is no sweep in the trailing edge and the planform area of the wing is 36 ft. Use V = 176 ft/sec at standard sea level. 1.39. The wing described in problem 1.38 is used as an aft horizontal stabilizer for the main wing described in problem 1.37. The root quarter-chord of the horizontal stabilizer is 15 feet aft of the quarter-chord of the main wing. Use the computer program from problem 1.36 to compute the lift at a 10-degree angle of attack and for each lifting surface in this wing-tail combination. Use V=176 ft/sec at standard sea level. Compare the results obtained with those obtained in problems 1.37 and 1.38 for each lifting surface in isolation. Discuss your findings.