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 of 0.8 which corresponds to τ = 0.054 and e = 0.95. Calculate the lift and induced drag coefficients for this wing at a geometric angle of attack of 3◦ . CL ≈ 0.37 and CDi ≈ 0.006.

correct me if i’m wrong but i believe it’s false

Oh yes igger daddy filled my loose ahοle with your sweet sweet mсum said ronald mcdonald as he spread his sesame covered mcahοle for thanos. thanos slid his throbbing purple ᑕock in to ronald's a. o screamed ronald as he poor hole was torn to bloody shreds. gunga gingagunga gingagunga gingagunga ginga a space ranger appeared making autistuc noises odio a los negros! said buzz lightyear as he aped them both.