Problem $06\mathrm{.}008-$ Estimate absolute ceiling

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 $\backslash (=3000\backslash$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 absolute ceiling of the airplane. Refer to the power plot of the airplane qiven below at sea level and at $12,000$ ft altitude.

The absolute ceiling of the single$-$engine light airplane is ft$.$