Induced Drag Experiment

tropnevad

Hi, i have been tasked to find out the induced drag of a a wing. I have measurements of lift and drag for a series of differant angles of attack. So what i did was i plotted Cl^2 and Cd, to give a nice plot.

My question is how will i find out the induced drag coefficient of this wing?.. is it the gradient of the line? as in Cd = Cd0 + kCl^2 where k is the induced drag coefficient?

Could someone care to explain if what i have done is correct?