solve it as a matlab code pls

The Drag $($FD$)$ and Lift $($FL$)$ forces of an aircraft can be estimated by the following formulas: $=122$ ; $=122$ is the air speed $($m$/$s$),$ is the wing span $($m$2),$ is the air density $($kg$/$ m$3)$ and $$ are the drag and lift coefficients. Both $$ and $$ depend on $($angle of attack$)$ and have the following correlations: $=8\mathrm{.}6510531\mathrm{.}571032+9\mathrm{.}21103+6\mathrm{.}9103=1\mathrm{.}2710439\mathrm{.}291042+1\mathrm{.}16101+3\mathrm{.}38101$ Where is in degrees For $=1\mathrm{.}225$ kg$/$ m$3,$ S $=3\mathrm{.}6$ m$2,$ V $(100$ values ranging from $20$ to $120),$ $(100$ values ranging from $0$ to $20)$; you are required to produce, exactly, the same following plot by completing the below MATLAB code. The main program contains all necessary input parameters then the above plot is created after calling two script sub$-$functions. The first function, called $$FDFL$,$ has two inputs $($ $,$ V$)$ and should returns the drag and lift forces $($FD $,$ FL$).$ The second function, called $$CDCL$,$ has one input $($ $)$ and returns two outputs, the coefficients $($CD $,$ CL$)$ Main program. $($Hint : write all given commands excluding the commented lines $(\%)$ then complete missing!$)$ clear; clc; format short g $\%$ Define the global variables $............................................................................\%$ Define the constant parameters: density, wing span, and the attack angles. rho$=.......$;$.......=.........$;alpha$1=.......$;$......=.......$;$......=.......$; $\%$ Define the parameters with a range of values V and alpha $------=--------------$; $--------=-------------$; $\%$ Call the function FDFL to calculate the drag and lift forces at different $\%$ attack angles $[$FD$1,$FL$1]=$FDFL$($alpha$1,$V$)$; $\%$ drag and lift for alpha$1[-----,-----]=-------(-----,----)$; $\%$ drag and lift for alpha$2[-----,-----]=-------(-----,----)$; $\%$ drag and lift for alpha$3\%$ Call the function CDCL to calculate the drag and lift coefficients $[-----,-----]=-------(-----)$; $\%$ Start the sub$-$plotting$---------------------------------------------------------\%$ first subplot $($Drag forces$)$ subplot$(2,2,1),-----------------------------------------------,---------\%$ Define labels and legend of the first subplot $---------------------------------------------------------------------------------------------------\%$ second subplot $($Lift forces$)$ subplot$(-----),----------------------------------------------------------\%$ Define labels and legend of the second subplot $---------------------------------------------------------------------------------------------------\%$ Third subplot $($Drag and Lift coefficients$)$ subplot$(--------),-------------------------------------------------------\%$ Define labels and legend of the third subplot $------------------------------------------------------------------\%$ add the second axis and plot for CL yyaxis $----------------------------------------------------------\%$ define the label and legend $------------------------------------------------------------------$ sub$-$functions $\%$ define the function FDFL function $[...,...]=$FDFL$(...,...)$ global $--------------------------------------\%$ call the function CDCL to calculate the drag and lift coefficients $[...,...]=------(-------)$; $\%$ Calculate the drag and lift forces $-----=------------------------------$; $-----=------------------------------$; End $\%$ define the function CDCL function $[---,---]=$CDCL$(-----)\%$ Calculate the drag and lift coefficient $-----=-----------------------------------------------------------------------$;