Fox and McDonald's Introduction to Fluid Mechanics
9th Edition
ISBN: 9781118912652
Author: Philip J. Pritchard, John W. Mitchell
Publisher: WILEY
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Textbook Question
Chapter 9, Problem 114P
If CL = 1.0 and CD = 0.05 for an airfoil, then find the span needed for a rectangular wing of 10 m chord to lift 3560 kN at a take-off speed of 282 km/h. What is the wing drag at take-off?
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Chapter 9 Solutions
Fox and McDonald's Introduction to Fluid Mechanics
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