Question

2. An aircraft with Coo -0.020, k0.12 is in steady, level flight at he -30,000 ft and Mo- me AR 08. The aircraft has a wing area of 375 ft, and it weighs 25,000 lb. Its CLmax İsl 8 a. b. c. d. e. Calculate the drag coefficient when Calculate the thrust the engine is producing. Calculate the horsepower the engine is producing Calculate the stall speed at that altitude Now the velocity is to be changed. Calculate the minimum thrust required and the velocity at which it occurs. 3. An airplane has the following characteristics: weight 3000 lb, wing area 181 ft, aspect ratio- 6.2, zero-lift drag coefficient = 0.027, and Oswald efficiency factor = 0.91 . The airplane is powered by a 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 of 0.83. The airplane is in steady, level flight. a. Calculate the minimum horsepower required and the velocity at which it occurs at sea level b. Calculate the maximum velocity at sea level c. Calculate the minimum horsepower required and the velocity at which it occurs at 10,000-ft altitude d. Calculate the maximum velocity at 10,000-ft altiude

Answer 1

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