The measured lift slope for the NACA 23012 airfoil is 0.1080 degree1, and L = 0 =

Question:

The measured lift slope for the NACA 23012 airfoil is 0.1080 degree–1, and αL = 0 = 1.3°. Consider a finite wing using this airfoil, with AR = 8 and taper ratio = 0.8. Assume that 8 = r. Calculate the lift and induced drag coefficients for this wing at a geometric angle of attack = 7°.