Consider the general aviation aircraft in steady level longitudinal flight at a constant altitude of 20,000 ft, with constant but not optimal values of the lift coefficient and the drag coefficient.
(a) Suppose that the range in this flight condition is 1,050 miles. What are the values of the lift coefficient and the drag coefficient? What is the corresponding time of flight?
(b) Suppose that the endurance in this flight condition is 23,200 s. What are the values of the lift coefficient and the drag coefficient? What is the corresponding range?