HW26 - chord point and equal to 8% of the chord. Angle of...

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AAE 334 Fall 2011, Homework 26 Due Friday, November 18 at the beginning of class. Use the shock-expansion method to compute the lift and drag coefficients for the airfoil sketched below in a Mach 1.8 flow. Chord length is c and maximum thickness is at the quarter-
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Unformatted text preview: chord point and equal to 8% of the chord. Angle of attack varies from 0 to 10 degrees. Use Matlab compressible flow files to save time. Hand in: 1. Written explanation of your method 2. Your m-file 3. Plot of the lift curve 4. Plot of the drag polar...
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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.

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