3. The equation of the mean camber line of the NACA 23012 is given by 3 2 Z C = 2.6595 [(*) -0.6075(*) * + +0.11471 For the region 0.0c ≤ x ≤0.2025c and Z с = 0.022083(1) for the region 0.2025c≤x≤ 1.000c. Calculate the A0, A1, and A2 for this airfoil section. Write the expression for the section lift coefficient. What is the angle of attack for zero lift? What is the angle of attack required to develop the design lift coefficient of 0.3? Calculate the section moment coefficient about the theoretical aerodynamic center. Compare your theoretical values with the experimental values from Abbott and von Doenhoff. When the geometric angle of attack is 3°, what is the section lift coefficient? What is the x/c location of the center of pressure?