Here is part of my code that I am having problems with: The induced angle is currently 21 different values across the wing span (the alpha is currently fixed). I want to compare the angle_eff with values from excel files to obtain the coefficient of lift. I am able to match the angle_eff with the first column of excel data (alpha), but then I need it to take the corresponding lift coef. as it's value. Part of the excel data is provide below followed by the code. Can anyone help? If you wish to view the entire code just ask.

`alpha Lift Coef.0 01 0.112 0.223 0.334 0.445 0.556 0.667 0.778 0.889 0.9910 1.0685angle_eff = (alpha - induced_angle);figure(6)plot(y,angle_eff)%read data in `

val1 = xlsread('NACA0015.xlsx');c1 = val1(:,1);angle_eff_round = round(angle_eff);display(c1)c2 = val1(:,2);%display(angle_eff_round)

num = length(c1);for i = 1:num cl_new = ismember(c1,angle_eff_round); %if cl_new == true

%end

end

%figure(7) %plot(y,cl_new)

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