Calculate the zero-lift angle of attack. b) Calculate the lift coefficient when α=5 degrees. c) If the airfoil is flipped upside down, what angle of attack is required to generate as much lift as in part (b)? d) Compare the results you obtained with experimental data for the NACA 4412 airfoil and note the percentage difference between theory and experiment. Where in your opinion lie the biggest discrepancies between theory and experiment?