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AAE 334 Fall 2011, Homework 26
Due Friday, November 18 at the beginning of class.
Use the shockexpansion 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 mfile 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.
 Fall '09
 COLLICOTT

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