In matlab, I need help with this problem.

This is what I have done so far regarding the two functions and script

The lift-to-drag ratio is an indication of the effectiveness of an airfoil. The following formula is commonly used by engineers to predict the lift-to-drag ratio of an airfoil L CL D CD where L and D are the lift and drag forces and CL and CD are the lift and drag coefficients. Both CL and CD depend on (angle of attack) the angle between the relative air flow direction (or air velocity direction) and the airfoil's chord line. Wind tunnel experiments for a particular airfoil have resulted in the following formulas: c.-447 10-,, + 1.15x10-V+666 x 10-1 + 102 x 10-' Cn = 5.75 10%, + 5.09 x 10-Y + 1.81 x 10-ta + 1.25 x 10-2 where is in degrees. (a) Define a function called CL and CD that accepts as an input and returns two outputs CL and CD (b) Define a second function called L _to_D that accepts two inputs, CL and CD, and returns the ratio CLI CD (c) Write a script file that ( i ) plots the lift-to-drag ratio for ranging between-2 and 22 at 0.1 increments (ii) find the maximum lift-to-drag ratio and the corresponding angle of attack, a Lift Drag Angle of atacik Relative tow direction Weight