function [xo,yo,R]=Circular_Chord_Quas_1d(thickness,c)
%%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)/(2*thickness);
R=sqrt(xo^2+yo^2);

R=roundn(R,-4);
yo=roundn(yo,-4);
xo=roundn(xo,-4);

%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]);