Hi guys, I got an aerodynamics exam next Monday and got stuck on something and was hoping that some expert from F1Technical might help.
I was going over one question we had where we had to find Cl, Cd, and Cm.
Now usually after finding Cl, we would find Cdi (induced) and Cd = Cd0 + Cdi.
But in this case we stopped at Cd = Cd0.
In actual fact we could not calculate Cdi in this particular case because we did not know the AR, span, or area, just the chord length.
Had we known the rest, should I have calculated the induced drag?
Ultimately, the question boils down to:
Cdi is not calculated for an infinite wing or because of the Mach number?