In some aerodynamic literature, the drag of an airplane is couched in terms of the "drag area" instead of the drag coefficient. By definition the drag area, f, is the area of a flat plate at 90° to the flow that has a drag force equal to the drag of the airplane. As part of this definition, the drag coefficient of the plate is assumed to be equal to 1, as shown in Prob. 5.31. If CD is the drag coefficient of the airplane based on wing planform area S, prove that f = CDS.
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