Problem $2.(45$ pts$)$ Consider a wing$-$fuselage model with $C_{m_{acos}}=-0\mathrm{.}022,x_{cg}=\frac{0\mathrm{.}33}{b}ar(c),x_{ac}=\frac{0\mathrm{.}22}{b}ar(c),$

$C_{L_{{}_{wf}}}=0\mathrm{.}08$ per degree. The area and mean chord of the wing are $0\mathrm{.}1m^2$ and $0\mathrm{.}1$ m $,$ respectively. Now

assume that a horizontal tail is added to this model. We have the following parameters: $l_t=0\mathrm{.}17m,$

$S_t=0\mathrm{.}02m^2,i_t=2\mathrm{.}7,C_{L_{{}_t}}=0\mathrm{.}1$ per degree, $=1,{}_0=0$ and del$\frac{}{d}el=0\mathrm{.}35$

$($c$)(10$ pts$)$ Calculate the neutral point location.

Problem $2.(45$ pts$)$ Consider a wing$-$fuselage model with $C_{m_{\text{a}\text{c}\text{m}\text{f}}}=-0\mathrm{.}022,x_{cg}=\frac{0\mathrm{.}33}{b}ar(c),x_{ac}=\frac{0\mathrm{.}22}{b}ar(c),$

$C_{L_{{}_{wf}}}=0\mathrm{.}08$ per degree. The area and mean chord of the wing are $0\mathrm{.}1m^2$ and $0\mathrm{.}1$ m $,$ respectively. Now

assume that a horizontal tail is added to this model. We have the following parameters: $l_t=0\mathrm{.}17m,$

$S_t=0\mathrm{.}02m^2,i_t=2\mathrm{.}7,C_{L_{at}}=0\mathrm{.}1$ per degree, $=1,{}_0=0$ and del$\frac{}{d}el=0\mathrm{.}35$

$($d$)(5$ pts$)$ Calculate the static margin.

$($c$)(10pts)$ Calculate the neutral point location.