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Unformatted text preview: Prof. Daniel J. Bodony AE311, Fall 2011 HW #6 Due 5 pm Wednesday, November 30, in the AE311 dropbox Problem 1 In thin airfoil theory we showed in class that the circulation distribution ( ) could be written as ( ) =- 2 U A 1 + cos sin + summationdisplay n = 1 A n sin( n ) where the airfoil has chord c , lies between x = 0 and x = c and the coordinate was related to x by x = c 2 (1- cos ) . If the airfoil camber line is y = ( x ) then the coe ffi cients A i are given by A = - 1 integraldisplay d d x ( ) d , A n = 2 integraldisplay d d x ( ) cos( n ) d n = 1 , 2 , . . . From these definitions, show that (a) The net circulation = c integraltext ( x ) d x is =- U c parenleftbigg A + A 1 2 parenrightbigg (b) The lift is L = U 2 c ( A + A 1 / 2)....
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This note was uploaded on 01/26/2012 for the course MUS 130 taught by Professor Lee during the Fall '08 term at University of Illinois, Urbana Champaign.
- Fall '08