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Unformatted text preview: September 12 version final corrected version. AAE 334, Fall 2011, Homework 7 SOLUTION Due Friday, September 9 at the beginning of class. The camber line, , of a thin airfoil of chord length c is given by the piecewise continuous function: ( ) x z c ( ) + = c x c for c x c x c x for c x c x c x z c 3 . 6 . 4 . 245 9 3 . 6 . 2 . Use the results of thin airfoil theory to solve (to two significant figures) for the: 1. section lift coefficient for flight at 4 degrees angle of attack. 2. pitching moment coefficient about the quarterchord point for flight at 4 degrees angle of attack. 3. The zerolift angle of attack in degrees. Show your work neatly with sufficient explanations of your method. Results of thin airfoil theory to use are: ( ) ( 1 2 2 L l A A c ) = = ( ) 1 2 4 / , 4 A A c c m = So to compute , , and , you need the slope of the camber line, A 1 A 2 A dx dz c : = c x c for c x c x for c x dx dz c 3 . 2 6 . 245 9 3 . 2 6 . 2 . Transform to o and combine terms: ( ) ( ) [ ] ( ) ( ) [ ] = = = c for for dx dz o o o o o o c 1 1 cos 1 6 . 245 9 cos 1 2 1 2 6 . 245 9 cos 1 2 . 12 . cos 1 2 1 2 6 . 2 ....
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 Fall '09
 COLLICOTT

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