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Forum: Main CFD Forum October 8, 2013, 14:22

Replies: 6 C4 airfoil data Views: 7,949 Posted By Ammofreak matlab code Here is the code to generate C4 thickness distribution and cambered airfoil clc clear all t = 0.1;%thickness, t and x are in % of chord length theta = 18.5*pi/180; %camber angle/2 mu =...

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