Consider the straight wing in problem $2,$ with aspect ratio of $7\mathrm{.}0,$ flying at M$=0\mathrm{.}85$ at

$12$km$.$ A NACA $0009$ airfoil section is used at all spanwise stations. For an equivalent wing

in incompressible flow, what is the airfoil section chord length $($c$)$ relative to the original

chord $($c$),$ and the aspect ratio? What is the corresponding thickness$-$to$-$chord ratio i$.$e$.$ what

NACA $000$# is representative? $($Round to the nearest integer.$)$