Consider a light, single-engine, propeller-driven airplane similar to a Cessna Skylane. The airplane weight is 1340 kg and the wing reference area is 17 m². The drag coefficient of the airplane CD is a function of the lift coefficient C this function for the given airplane is: Cp = 0.025 +0.054C²ₗ. For a steady level flight at sea level, where the ambient atmospheric density is 1.23 kg/m³, plot on a graph the variation of CL, CD, and the lift-to-drag ratio L/D with flight velocity ranging between 10 m/s and 120 m/s. Write some interpretations from your results.