A rectangular airfoil of (40 mathrm{ft}) span and (6 mathrm{ft}) chord has lift and drag coefficients of
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A rectangular airfoil of \(40 \mathrm{ft}\) span and \(6 \mathrm{ft}\) chord has lift and drag coefficients of 0.5 and 0.04 , respectively, at an angle of attack of \(6^{\circ}\). Calculate the drag and horsepower necessary to drive this airfoil at 50,100, and \(150 \mathrm{mph}\) horizontally through still air \(\left(40^{\circ} \mathrm{F}\right.\) and 13.5 psia). What lift forces are obtained at these speeds?
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Related Book For
Fox And McDonald's Introduction To Fluid Mechanics
ISBN: 9781118912652
9th Edition
Authors: Philip J. Pritchard, John W. Mitchell
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