Fundamentals of Aerodynamics
Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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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 ft 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 + 0.054 C L 2 .

a. For a steady level flight at sea level, where the ambient atmospheric density is 0.00 2377 slug / ft 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.

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