function [xo,yo,R]=Circular_Chord_Quas_1d(thickness,c,offset) %%This will try and get the equation for the surface that we're using %%as our airfoil %% %%It is a circular chord that has the following points %% (0,0) (c/2,.03c) (c,0) %% %%The form is a circle equation %% R^2=(x-xo)^2+(y-yo)^2 xo=c/2; yo=-(xo^2-thickness^2)/(0.06*c) R=sqrt(xo^2+yo^2); %yo=-4.15166*c; R=sqrt(17.4863*c); %%Plot it out %%x=[-5:0.01:5]; %%ytop=sqrt(R^2-(x-xo).^2)+yo; %%ybottom=-sqrt(R^2-(x-xo).^2)+yo; %plot(x,ytop,x,ybottom); %axis([-5 5 -9.9 .1]); %dy_ds=-(x-c/2)./sqrt(R^2-(x-c/2).^2); %plot(x,dy_ds); %axis([0 1 -.2 .2]);