HW7 - 1. section lift coefficient for flight at 4 degrees...

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AAE 334, Fall 2011, Homework 7 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 . 0 6 . 0 4 . 0 490 18 3 . 0 0 6 . 0 2 . 0 Use the results of thin airfoil theory to solve (to two significant figures) for the:
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Unformatted text preview: 1. section lift coefficient for flight at 4 degrees angle of attack. 2. pitching moment coefficient about the quarter-chord point for flight at 4 degrees angle of attack. 3. The zero-lift angle of attack in degrees. Show your work neatly with sufficient explanations of your method....
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This note was uploaded on 02/21/2012 for the course AAE 334 taught by Professor Collicott during the Fall '09 term at Purdue University-West Lafayette.

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