Chapter 1, Problem 1.15P

Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylanc. The airplane weight is 2950 lb and the wing reference area is $174{\text{ft}}^{\text{2}}$. The drag coefficient of the airplane $C_D$ isa function of the lift coefficient $C_L$ for reasons that are given in Chapter 5; this function for the given airplane is $C_D=0.0250+0.054C_L^2$.

a. For a steady level flight at sea level, where the ambient atmospheric density is $0.00\text{2377 slug}/{\text{ft}}^{\text{3}}$. plot on a graph the variation of $C_L$, $C_D$, and the lift-to-drag ratio LID with flight velocity ranging between 70 ft/s and 250 ft/s.

b. Make some observations about the variation of these quantities with velocity.