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Unformatted text preview: 1 1 1 2 2 1 2 1 2 1 1 2 1 / 2 2 1 / 2 2 , cr cr cr cr cr p M M M M c In Matlab, I just used a few lines: % hw32.m % gam = 1.4; % ratio of specific heats cpo = [2.738 3.691 2.037]; % Cpo values Mcr = [NaN NaN NaN]; % for i = 1:3 Mcr(i) = fzero(@(x) (cpo(i)/sqrt(1x^2))((2/(gam*x^2))* ... (((2+(gam1)*x^2)/(gam+1))^(gam/(gam1))1)), 0.2 ); end Critical pressure coefficient values are not asked for but are found this way: cpcr = cpo ./ sqrt(1Mcr.^2) (data and figure below from “Airfoil modification effects on subsonic and transonic pressure distributions and performance for the EA6B airplane,” Allison, Dennis O. and Sewall, William G., NASA Langley Research Center, NASATP3516, 1995.)...
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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.
 Fall '09
 COLLICOTT

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