How to use vortex panel method on Joukowski airfoil?

I'm trying to figure out how to use the vortex panel method to plot the pressure distribution over a Joukowski airfoil. I also need to compute the lift and drag and plot the streamlines. So far I have the paneled airfoil, lift, and the pressure distribution. How do I get the streamlines?

Here's my code:

%inputs U=1; a=1; b=0.8; y1p=0.199; theta=linspace(0,2*pi,22); rho=1.225;

%airfoil x1p=b-sqrt(a^2-y1p^2); z1p=x1p+1i*y1p; z2=a*cos(theta)+a*1i*sin(theta); z1=z2+z1p; z=z1+(b^2)./z1; w=U*(z2+(a^2./z2)+1i*2*y1p*log(z2./a)); LIFT=rho*U*4*pi*y1p*U; display(LIFT, 'Lift force (N)');

%pressure coefficient i=1; while i<23 V(1,i)=U*abs((1-(a/z2(1,i))^2+1i*2*y1p/z2(1,i))/(1-(b/z1(1,i))^2)); Cp(1,i)=1-(V(1,i)/U)^2; i=i+1; end

figure(1) plot(z,'k-') axis([-3 3 -3 3])

figure(2) plot(real(z),real(Cp),'k-')