Question $1$

Consider a linearly tapered wing with a total span of $12\mathrm{.}192$ m $,$ with a chord length, $\backslash ($ c $\backslash ),$ sectional lift slope, $\backslash (\backslash$frac$\{\backslash$partial C$\_\{$L$\}\}\{\backslash$partial $\backslash$alpha$\}\backslash ),$ and sectional angle of incidence, $\backslash (\backslash$alpha $\backslash ),$ which all vary linearly from the mid$-$span to the wing tips.

The wing is flying straight and level at $\backslash (89\mathrm{.}4\backslash$mathrm$\{$~m$\}/\backslash$mathrm$\{$s$\}\backslash ).$

$($a$)$ Calculate the wing area and aspect ratio.

$($b$)$ Determine the circulation distribution for this wing.

$($c$)$ Calculate the lift coefficient and induced drag coefficient for this. Wing.

$($d$)$ How does the induced drag factor for this wing compare with an untwisted wing with a constant aerofoil section?