A turbojet engine is cruising at M$\_($a$)=0\mathrm{.}9$

at an altitude of $11$ km $.$ The engine characteristics are

such that the compressor, burner, and turbine efficiencies

may be taken as $\backslash$eta $\_($c$)=0\mathrm{.}85,\backslash$eta $\_($b$)=0\mathrm{.}96,$ and $\backslash$eta $\_($t$)=0\mathrm{.}90,$

respectively, and the mechanical shaft efficiency between

the turbine and the compressor is $\backslash$eta $\_($m$)=100\%.$ The total

inlet pressure recovery may be taken as $\backslash$pi $\_($d$)=1\mathrm{.}0$ and the

mass flow captured by the inlet is m$\_($a$)^()=29\mathrm{.}17$k$($g$)/($s$).$ The

fuel used has a heating value of the fuel is $10,516$ca$($l$)/($g$)$m$.$ The compressor pressure ratio

is $\backslash$pi $\_($c$)=18,$ the combustor pressure loss is $($p$\_($t$3)-$p$\_($t$4))=0\mathrm{.}02$p$\_($t$3),$ and the turbine inlet

temperature is T$\_($t$4)=1,330$Kp$\_(8)=$p$\_($a$)$ and

$\{$:$\backslash$eta $\_($n$)=1\mathrm{.}00),$ what is the net thrust?