Q#$2(25$ pts$)$

The wing$-$fuselage of an aircraft has been designed with following characteristics:

$S=225f{t}^2$;$,C_{L_{}}=0\mathrm{.}105\frac{1}{\text{d}\text{e}\text{g}}$;$i_w=1\mathrm{.}5$;$\frac{x_{cg}}{(\frac{?}{\text{b}\text{a}\text{r}}(c))}=\frac{0\mathrm{.}25}{b}ar(c)$;$,C_{w_f}=0\mathrm{.}05+0\mathrm{.}005{}^0$;$,AR=7\mathrm{.}5,C_w=0\mathrm{.}15.\frac{?}{b}$

$ar(c)=5ft.$

Design the horizontal tail $(V_H,i_t)$ so that aircraft has the pitch stability of $C_m=0\mathrm{.}15-{0\mathrm{.}032}^D$

$A{R}_t=4\mathrm{.}5$;$C_{L_t}=0\mathrm{.}09\frac{1}{\text{d}\text{e}\text{g}}.$ What is the tail area if the distance between the tail ocerodynamic $4$ eg is $15$ ft $?$