HW1 soln

HW1 soln - pressures on the upper and lower surfaces are...

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MEM 420: Aerodynamics Spring 2010-2011 Homework #1 Due: April 07, 2011 Problem 1 : (#1.5 in Ed. IV) Consider an airfoil at 12 o angle of attack. The normal and axial force coefficients are 1.2 and 0.03, respectively. Calculate the lift and drag coefficients. Problem 2 : (#1.3 in Ed. IV) Consider an infinitely thin flat plate of chord c at an angle of attack of α in a supersonic flow. The
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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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HW1 soln - pressures on the upper and lower surfaces are...

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