$2.$ Consider a Joukowski mapping with a mapping constant $\backslash (\backslash$mathrm$\{$C$\}=1\backslash ).$ The thickness, $\backslash ($ t $\backslash ),$ of a Joukowski airfoil generated using this mapping can be determined, to a fair approximation, by placing the mapping circle a distance $\backslash (0\mathrm{.}7698($t $/$ c$)\backslash )$ to the left of the imaginary axis. Write a Matlab program to generate and plot Joukowski airfoil sections and the pressure distributions they produce as a function of the thickness and zero lift angle of attack. Plot Joukowski airfoil shapes $($in their true aspect ratio$)$ and the pressure distributions they produce at $3$ degrees angle of attack $($with $-$Cp plotted vs$.$ x$/$c$,$ with x measured from the leading edge$)$ for the following combination of thickness to chord ratio and zero lift angle of attack: $($a$)10\backslash \%$ and $-3$ degrees, $($b$)18\backslash \%$ and $-5$ degrees. Include with your plots the values of the lift coefficients obtained from the analytic formula. Submit a copy of your code and the plots with your solution.