$\frac{T}{W_0}=0\mathrm{.}4$

$\frac{W_0}{S}=60\mathrm{.}0l\frac{b}{f}{t}^2$

Aspect Ratio $=7\mathrm{.}0$

$C_{D,0}=0\mathrm{.}022$

$e=0\mathrm{.}7$

$C_{\text{c}\text{r}\text{u}\text{i}\text{s}\text{e}}=0\mathrm{.}55l\frac{b}{h}r-lb,\frac{W_{\text{c}\text{r}\text{u}\text{i}\text{s}\text{e}}}{S}={0\mathrm{.}85}^{*}\frac{W_0}{S}$

$C_{\text{l}\text{o}\text{i}\text{t}\text{e}\text{r}}=0\mathrm{.}45l\frac{b}{h}r-lb,\frac{W_{\text{l}\text{o}\text{i}\text{t}\text{e}\text{r}}}{S}=0\mathrm{.}80*\frac{W_0}{S}$

$M_{\text{m}\text{a}\text{x}}=0\mathrm{.}8,$

$M_{\text{c}\text{r}\text{u}\text{i}\text{s}\text{e}}=0\mathrm{.}7,$

Crew: $2$ pilots each weighing $175$ lbs $,$ plus $25$ lbs of luggage per pilot

Additional Payload: $3000$ lbs

Note:

L$/$D can be solved for both cruise and loiter using the following equation:

$\frac{L}{D}=\frac{1}{\frac{q{C}_{D0}}{\frac{W}{S}}+\frac{\frac{W}{S}}{qAe}}$

Assume cruise altitude is a constant $30,000ft$

Determine $V_{\text{l}\text{o}\text{i}\text{t}\text{e}\text{r}}$ by maximizing L$/$D at the cruise altitude

When calculating mission fuel fractions, assume:

$\frac{W_1}{W_0}=0\mathrm{.}97$

$\frac{W_2}{W_1}=0\mathrm{.}98$

$\frac{W_5}{W_4}=0\mathrm{.}99$

$\frac{W_6}{W_5}=0\mathrm{.}992$

To calculate $\frac{W_e}{W_0},$ use the "jet transport" a$,$ b$,$ and C coefficients in Raymer Table $6\mathrm{.}1$

Starting with an initial guess of $W_0=14,500lbs,$ approximate $W_0$ by using the successive

approximation iteration method with the following equation and write out the result you

get after $3$ iterations:

$W_0=\frac{W_{\text{h}\text{u}\text{m}\text{a}\text{n}}+W_{\text{p}\text{a}\text{y}\text{l}\text{o}\text{a}\text{d}}}{1-(\frac{W_{\text{e}\text{m}\text{p}\text{t}\text{y}}}{W_0})-(\frac{W_{\text{f}\text{u}\text{e}\text{l}}}{W_0})}$ where $\frac{W_{\text{f}\text{u}\text{e}\text{l}}}{W_0}=1\mathrm{.}06(1-\frac{W_x}{W_0})$