An engine has been designed for a V$/$STOL aircraft. The maximum take off $($MTO$)$ weight in Vertical Take Off $($VTO$)$ condition is $9415$ kg $.$ Assuming the engine is designed for maximum thrust in VTO condition, compute the exhaust velocity when the vehicle is flying at its top speed of $1083k\frac{m}{h}r.$ The engine is a low$-$bypass turbofan with a bypass ratio of $1\mathrm{.}2,$ maximum incoming airflow of $196k\frac{g}{s}$ and fuel air ratio of $0\mathrm{.}03$ at maximum thrust. Assume exhaust velocity for both streams is the same.