Problem $5[2$ points$]$ Consider an airplane patterned after the Beechcraft Bonanza V$-$tailed, single$-$engine light private airplane, whose characteristics are as follows.

Wing geometry: $AR=6\mathrm{.}2,S=16\mathrm{.}82m^2$

Normal gross weight: $W_0=14,324N$

Parasite drag coefficient: $C_{D_0}=0\mathrm{.}027$

Oswald efficiency factor: $e=0\mathrm{.}91$

Power plant: Single piston engine with $P_{\text{m}\text{a}\text{x}}=257\mathrm{.}27{10}^3$ Watt at sea level, and $=0\mathrm{.}83$ for the two$-$blade propeller

Specific fuel consumption: $c=6\mathrm{.}959{10}^{-7}\frac{N}{W*s}$

Fuel weight: $W_f=1,104N$

$5\mathrm{.}1$ Estimate the sea$-$level liftoff distance, assuming a paved runway with the friction coefficient during take$-$off ${}_{LO}=0\mathrm{.}02$ and the maximum lift coefficient during the ground roll is $1\mathrm{.}1.$ When the airplane is on the ground, the wings are $1\mathrm{.}22$ m above the ground. Note that $(P_A{)}_{\text{m}\text{a}\text{x}}=P_{\text{m}\text{a}\text{x}}=T_{\text{m}\text{a}\text{x}}{V}_{}$ for a propeller$-$driven airplane. $($Answer: $S_{LO}=210$ m $)$

$5\mathrm{.}2$ Estimate the sea$-$level landing ground roll distance, assuming that the fuel is almost fully used up before landing $($i$.$e$.,$ empty weight$)$ and the maximum lift coefficient with flaps at touchdown is $1\mathrm{.}8.$ After touchdown, assume zero lift and off ${}_L=0\mathrm{.}4.$ Finally, when a thrust reversal device and parachutes are utilized to reduce the landing distance, determine the minimum sum of thrust reversal and additional drag required to have the sea$-$level landing distance less than $120$ m $.($Answer: $S_L=149m$;$(T_r+D^{\text{'}}{)}_{\text{m}\text{i}\text{n}}=1,317\mathrm{.}6N)$