The RQ$-4$ Global Hawk is a high$-$altitude, long$-$endurance aircraft. The wingspan of the RQ$-4$ is $39\mathrm{.}9$ m$,$ and the wing area is $50\mathrm{.}1$ m$2.$ The maximum take$-$off mass is $14628$ kg$,$ and the maximum fuel mass is $7847$ kg$.$ The powerplant is a Rolls$-$Royce F$137$ turbofan engine that produces $34$ kN of thrust at sea level, and $8658$ N of thrust at hg $=12,000$ m$.$ Assume that the Oswald efficiency factor is $0\mathrm{.}79,$ the zero$-$lift drag coefficient is $0\mathrm{.}032,$ and the thrust specific fuel consumption is $1\mathrm{.}00$E$-4$ s$-1$ at sea level and $1\mathrm{.}84$E$-4$ s$-1$ at hg $=12,000$ m$.$ Calculate the maximum velocity of the Global Hawk at sea level with full fuel.