Chapter 5, Problem 5.3P

The measured lift slope for the NACA 23012 airfoil is 0.1080 degree ${}^{-1}$, and ${\alpha }_{L=0}=-1.3°$. Consider a finite wing using this airfoil, with $AR=8$ and taper ratio $=0.8$. Assume that $\delta =\tau$. Calculate the lift and induced drag coefficients for this wing at a geometric angle of attack $=7°$.