aero_coeff.m

function [cl,cd,cm] = aero_coeff(x,y,cp,al,npanel)

cl = 0;
cd = 0;
cm = 0;

for i=1:npanel
    dx  = x(i+1) -x(i);
    dy  = y(i+1) -y(i);
    xa  = 0.5*(x(i+1) +x(i)) -0.25;
    ya  = 0.5*(y(i+1) +y(i));
    dcl = -cp(i)*dx;
    dcd = cp(i)*dy;
    cl  = cl +dcl;
    cd  = cd +dcd;
    cm  = cm +dcd*ya -dcl*xa;
end

dcl = cl*cos(al) -cd*sin(al);
cd  = cl*sin(al) +cd*cos(al);
cl  = dcl;


return