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Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylane. The airplane weight is 2950 lb and the wing reference area is 174 ft. The drag coefficient of the airplane CD is a function of the lift coefficient Cz; this function for the given airplane is CD = 0.025 + 0.054C?. For a steady level flight at sea level, where the ambient atmospheric density is 0.002377 slug/ fts, plot on a graph the variation of CL, CD, and the lift-to-drag ratio L/D with flight velocity ranging between 70 ft/s and 250 ft/s. Explain the variation of these quantities with velocity