If (C_{L}=1.0) and (C_{D}=0.05) for an airfoil, then find the span needed for a rectangular wing of
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If \(C_{L}=1.0\) and \(C_{D}=0.05\) for an airfoil, then find the span needed for a rectangular wing of \(10 \mathrm{~m}\) chord to lift \(3560 \mathrm{kN}\) at a take-off speed of \(282 \mathrm{~km} / \mathrm{h}\). What is the wing drag at take-off?
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Fox And McDonald's Introduction To Fluid Mechanics
ISBN: 9781118912652
9th Edition
Authors: Philip J. Pritchard, John W. Mitchell
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