Consider a Joukowski mapping with a mapping constant $C=1.$ The thickness of a Joukowski airfoil generated using this mapping can be determined, to a fair approximation, by placing the mapping circle a distance $0\mathrm{.}7698(\frac{t}{c})$ 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. Add additional code to numerically integrate the lift coefficient on the airfoil and compare the result with the analytic solution $($use $360$ points on the cylinder$/$airfoil$).$ Do not neglect the finite thickness of the airfoil in your integration. 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$.\frac{x}{c},$ with $x$ measured from the leading edge$)$ for the following combination of thickness to chord ratio and zero lift angle of attack: $($a$)10\%$ and $-3$ degrees, $($b$)18\%$ and $-5$ degrees. Include with your plots the values of the lift coefficients obtained by integration and from the analytic formula and the actual thickness achieved $($compared to the intended value$).$ Submit a copy of your code and the plots with your solution.