Consider a wing with a thin, symmetric airfoil section in a Mach $2$ airflow at an angle

of attack of $1\mathrm{.}5.$ Calculate the lift cofficient

$($a$)$ For the airfoil section.

$($b$)$ For the wing if it is a straight wing with an aspect ratio of $2\mathrm{.}56.$

$($c$)$ For the wing if it is swept at an angle of $60,$ with an aspect ratio of $2\mathrm{.}56$ and a taper

ratio of unity. $[$Note: These are approximately the characteristics of the wing for the

BAC $($English Electric$)$ Lightning supersonic fighter designed and built in England

during the $1960$s$.]$

$a_{\text{c}\text{o}\text{m}\text{p}}=\frac{4}{\sqrt[\phantom{2}]{M_{}^2-1}}$

$a_{\text{c}\text{o}\text{m}\text{p}}=\frac{4}{\sqrt[\phantom{2}]{M_{}^2-1}}(1-\frac{1}{2AR\sqrt[\phantom{2}]{M_{}^2-1}})$