Problem 1 Use XFOIL to determine the aerodynamic characteristics of the NACA 2412 airfoil at a Reynolds number of 5.7 x 10%. Plot the lift coefficient and pitching moment coefficient as a function of angle of attack, and the drag polar (i.e. c, vs. Ca). Compare the results with the experimental data reported in Abbott and von Doenhoff given below. 9 Section 8 casiois 28 Section ach ar attack, deg BACA 243 Weg Betion Section yo