Please use matlab to solve this question (I need the code)

60. The lift-to-drag ratio is an indication of the effectiveness of an airfoil. Re- ferring to Problem 59, the equations for lift and drag are where, for a particular airfoil, the lift and drag coefficients versus angle of attack are given by Cp = 5.75 10-63 + 5.09 10-42 + 1.81 10-4 + 1.25 10-2 Using the first two equations, we see that the lift-to-drag ratio is given simply by the ratio C1CD. Plot L/D versus for-20- maximizes LID. 22. Determine the angle of attack that