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From the rate-of-climb information for the single-engine light plane in Prob. 6.6, estimate the absolute ceiling of the airplane. (Again make the linear assumption described in Prob. 6.7.) Prob. 6.6 From the information generated in Pro b. 6.4, calculate the maximum rate of climb for the single-engine light plane at sea level and at 12,000-ft altitude. Pro b. 6.4 Consider an airplane patterned after the Beechcraft Bonanza V-tailed, single engine light private airplane. The characteristics of the airplane are as follows: aspect ratio = 6.2, wing area = 181 ft2, Oswald efficiency factor = 0.91, weight = 3000 , and zero-lift drag coefficient = 0.027. The airplane is powered by a single piston engine of 345 hp maximum at sea level. Assume that the power of the engine is proportional to free-stream density. The two-blade propeller has an efficiency of0.83. a. Calculate the power required at sea level. b. Calculate the maximum velocity at sea level. c. Calculate the power required at 12,000-ft altitude. d. Calculate the maximum velocity at 12,000-ft altitude. Prob. 6.7.) From the rate-of-climb information for the twin-jet aircraft in Prob. 6.5, estimate the absolute ceiling of the airplane. Prob. 6.5 From the information generated in Prob. 6.3, calculate the maximum rate of climb for the twin-jet aircraft at sea level and at an altitude of 5 km. Prob. 6.3 Consider an airplane patterned after the Fairchild Republic A-1 0, a twin-jet attack aircraft. The airplane has the following characteristics: wing area = 47m2, aspect ratio = 6.5, Oswald efficiency factor = 0.87, weight = 103, 047N, and zero-lift drag coefficient = 0.032. The airplane is equipped with two jet engines with 40,298 N of static thrust each at sea level. a. Calculate and plot the power-required curve at sea level. b. Calculate the maximum velocity at sea level. c. Calculate and plot the power-required curve at 5-km altitude. d. Calculate the maximum velocity at 5-km altitude. {Assume the engine thrust varies directly with free-stream density.)

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