For this problem, you are going to calculate the takeoff distance at sea level. Ignore ground effect.

Wing Area 330ft^2

Aspect Ratio 9

Take off weight 20,000 lb

 

A. List the wing area, aspect ratio, and takeoff weight B. Assume you have a takeoff thrust that is equal to 0.25 times the takeoff weight. Calculate the takeoff thrust. C. With takeoff flaps deployed, the CLmax speed, liftoff airspeed, and 0.7VLO. D. Assume that your airplane has a CDo 0.027 and an Oswald efficiency factor of 0.7. Write the drag polar equation for the full airplane. E. Calculate the drag and lift during takeoff. F. Using a friction coefficient of 0.026, calculate the takeoff distance. = - 2.5. Calculate the stall