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Unformatted text preview: pressures on the upper and lower surfaces are different but constant over each surface; that is p u (s) = c 1 and p l (s) = c 2 , where c 1 and c 2 are constants and c 2 > c 1 . Ignoring the shear stress, calculate the location of the center of pressure. (Read section 1.6 for center of pressure) solution Problem 1 : (#1.5 in Ed. IV) Problem 2 : (#1.3 in Ed. IV)...
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 Spring '11
 ajamal
 Force, Aerodynamics, Lift, Airfoil, drag coefficients, axial force coefficients

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