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 $(c^{\text{'}})$ 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.$)$