
#1
Apr1409, 06:48 AM

P: 2

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? 


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