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f22_ps15_fall03 - Fall 2003 Unified Engineering Fluids...

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Unformatted text preview: Fall 2003 Unified Engineering Fluids Problem F22 F22. A long rectangular wing has span b and chord c, and hence the wing area is S = bc. a) The wing airfoil has certain lift and drag coefficients c and cd which are constant across the span. Determine how these relate to the wing’s overall CL and CD . (Hint: Determine L and D , then get L and D , then from these determine CL and CD ). The wing airfoil has a drag p olar which can be approximated by cd 0.01 + 0.015 c3 in the range c = 0.1 . . . 1.2. The propulsive power P needed to overcome drag D at flight speed V∞ is given by P = D V∞ P cl 1.0 ? 0.5 0.0 0.01 0.02 cd V b) Determine the form of the P (V∞ ) relation in level flight, and plot it for the range c = 0.1 . . . 1.2. Any constant multiplicative factors on the P and V∞ axes are not important – only the shape of the curve is of interest. Hint: Simplest approach is to plot P (c ) versus V (c ) with c as a dummy parameter. (Note: Using only the airfoil’s cd ignores other contributions such as induced drag, which b ecome especially significant at low flight speeds!) ...
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