$4\mathrm{.}2$ Starting with the generalized thrust equation, Eq$.(4\mathrm{.}5),$ find the uninstalled thrust $($lbf$)$ and uninstalled thrust specific fuel consumption $(\frac{1}{h}r)$ of a mixed$-$flow afterburning turbofan engine on a test stand in

a$)$ Military power $($maximum nonafterburning power$)$

b$)$ Maximum power $($maximum afterburner$)$

The following performance parameters as determined by test measurements are known.

$m_0^{}=350lb\frac{m}{s},m_{f\text{m}\text{i}\text{l}}^{}=2\mathrm{.}715lb\frac{m}{s},m_{f,\text{m}\text{a}\text{x}}^{}=21\mathrm{.}033lb\frac{m}{s}$

$T_{t9\text{m}\text{i}\text{l}}=1097R,T_{9\text{m}\text{i}\text{l}}=904R,T_{t9\text{m}\text{a}\text{x}}=3400R,T_{9\text{m}\text{a}\text{x}}=2889R$