Q4 An airfoil 5 digits Naca series 23012 immersed in the flow field with the incoming free stream makes 5 angle of attack with respect to the airfoil's chord line. The camber line of this airfoil is given as: 2 5 [(+) -0.6075 (+) + 0.1147 ] for 0 0.2025 (a) (b) (c) (d) = 2.6595 0.2208 (1) for 0.2025 1.0 Using Thin airfoil theory, determine : the thin airfoil coefficient A0, A and A. the lift coefficient C. The pitching moment coefficient at the leading edge Cmle; and The center of pressure Cp. (10 marks) (4 marks) (3 marks) (3 marks)