Problem 2. [20 points] Consider flow of a uniform stream of speed V at an angle of attack a past the thin airfoil shown below with a parabolic camber line given by: z(x) = 4-(1-2) where is the maximum camber and < < c. (a) Find expressions for the lift coefficient (cp), zero-lift angle of attack (L=0), and moment coefficient about the leading edge (cm,LE). (b) Calculate values of the 3 parameters in Part (a) for = 4 and /c = 0.02. (c) Find the location of the center of pressure, xcp/c, for = 0 and 4 and /c = = 0.02.