The curves CD$,\backslash$alpha and Cm$,$ CG for a light aircraft are shown in Figure$($a$).$ The aircraft weight is $8000$ N$,$ its wing area $14\mathrm{.}5$m$2$ and its mean chord $1\mathrm{.}35$ m$.$ Determine the lift, drag, tail load and forward inertia force for a symmetric manoeuvre corresponding to n$=4\mathrm{.}5$ and a speed of $60$ m$/$s$.$ Assume that engine$-$off conditions apply and that the air density is $1\mathrm{.}223$ kg$/$m$3.$ Figure $14\mathrm{.}8($b$)$ shows the relevant aircraft dimensions. The correct answers are lift$=35,000$N$,$ Drag $=2,790$N Tail load$=1,000$ N Forward Inertia force $2,790$N