Consider an airplane patterned after the Beechcraft Bonanza V$-$tailed, single$-$engine light private airplane. The characteristics of the airplane are as follows: aspect ratio $\backslash (=6\mathrm{.}2\backslash ),$ wing area $\backslash (=181\backslash$mathrm$\{$ft$\}^\{2\}\backslash ),$ Oswald efficiency factor $\backslash (=0\mathrm{.}91\backslash ),$ weight $\backslash (=3500\backslash$mathrm$\{$lb$\}\backslash ),$ and zero$-$lift drag coefficient $\backslash (=0\mathrm{.}027\backslash ).$ The airplane is powered by a single piston engine of $345$ hp maximum at sea level. Assume the power of the engine is proportional to free$-$stream density. The two$-$blade propeller has an efficiency of $0\mathrm{.}83.$ Estimate the sea level landing ground roll distance for the airplane. Assume that the airplane is landing at full gross weight. The maximum lift coefficient with flaps at touchdown is $1\mathrm{.}8.$ Assume the coefficient of rolling friction $\backslash (\backslash$mu$\_\{$r$\}=0\mathrm{.}4\backslash ).$ After touchdown, assume zero lift. $($Round the final answer to the nearest whole number.$)$

The sea level landing ground roll distance for the airplane is