Here is the code to generate C4 thickness distribution and cambered airfoilclcclear allt = 0.1;%thickness, t and x are in % of chord length theta = 18.5*pi/180; %camber angle/2 mu = pi/6;%it is actually dy_c/dx, for simplicity i used it equal to 30 degrees.x = 0:0.02:1;y = (t/0.2)*(0.3048*x.^0.5-0.0914*x-0.8614*x.^2+2.1236*x.^3-2.9163*x.^4+1.9744*x.^5-0.5231*x.^6);%equation for symmetric airfoil C4y_c = sqrt(((0.5/sin(theta/2)).^2-(x-0.5).^2))-0.5/tan(theta/2);%equation of camber line %for upper s/f wrapped co-ordinates around camber line y_cx_u = transpose(115*(x-y*sin(mu)));y_u = transpose(115*(y_c+y*cos(mu)));%for lower s/f wrapped co-ordinates around camber line y_cx_L = transpose(115*(x-y*cos(mu)));y_L = transpose(115*(y_c-y*sin(mu)));plot(x_u,y_u,x_L,y_L);ylim([-20 50]);regards,Ammofreak