Aircraft A$,$ weighing $250,000$ lb$,$ is flying at an altitude of $36,000$ ft and a speed of $774\mathrm{.}363$ ft$/$s when it loses power from one engine due to a failure. The equivalent increase in minimum drag is ACD, $=0\mathrm{.}01,$ caused by deflection of the flight controls and engine displacement due to the wind. To what altitude must the aircraft descend to maintain its flight speed $(774\mathrm{.}363$ feet$/$second$)$ and the maximum available thrust from a single engine $($at $36,000$ ft$)?$ Consider an m value of $0\mathrm{.}6$ AIRCRAFT CHARACTERISTICS

Assume TSFC to be constant with altitude.

Assume thrust variation with altitude as $T_{\text{a}\text{l}\text{t}}=T_{sl}\sqrt[\phantom{2}]{\frac{{}_{sl}}{{}_{\text{a}\text{l}\text{t}}}}$