Consider the Viper Jet Mk$2$:

Takeoff Weight $=5,100$ lbf$.$

Fuel Weight $=1,700$ lbf$.$

Maximum Thrust at Sea Level: $2,850$ lbf$.$

$C_{D_0}=0\mathrm{.}0157$;$S=114\mathrm{.}1f{t}^2$;$e=0\mathrm{.}845$;$AR=6\mathrm{.}79$;$,TSFC=\frac{0\mathrm{.}981}{h}r$

$1.$ Calculate its $C_L$ for the best L$/$D$.$

$2.$ Calculate its $C_L$ for the best range.

$3.$ Calculate its maximum L$/$D$.$

$4.$ Calculate its velocity for hest $\frac{R}{C}$ at a weight of $4,250lbf.$ and standard sea level conditions.

$5.$ Calculate the $\frac{R}{C}$ at the velocity of the previous question.

$6.$ Calculate its velocity for best L$/$D at a weight of $4,250lbf.$ and standard sea level conditions.

$7.$ How much thrust does it need from the engine to maintain the flight regime of the previous question?

$8.$ Calculate its velocity for the best range at the same weight and an altitude of $30,000ft.$

$9.$ Calculate the best range of the aircraft if it uses the first $5\%$ of fuel during warm$-$up$,$ take$-$off, climb to cruise altitude, and $3\%$ remains for landing as reserve. Assume an initial cruise altitude of $30,000ft.$

$10.$ Calculate the best endurance of the aircraft at sea level, with only the reserve fuel.