QUESTION $-1$

A ramjet engine operates at a flight Mach number $M_0=0\mathrm{.}8$ at $9000$ m altitude where $p_0=30\mathrm{.}14$ kPa and $T_0=229K.$ For an effective exhaust velocity $V_e=760\frac{m}{s}$ and inlet cross$-$sectional area $A_1=0\mathrm{.}187m^2$ calculate;

$($a$)$ the air mass flow rate $m_0^{},$

$($b$)$ the fuel mass flow rate $m_f^{}$ for a fuel$-$to$-$air ratio of $\frac{f}{a}=0\mathrm{.}03,$

$($c$)$ the exhaust gas mass flow rate me$,$

$($d$)$ the gross thrust,

$($e$)$ the net thrust,

$($f$)$ the thrust power,

$($g$)$ the propulsive efficiency ${}_p,$

$($h$)$ the thermal efficiency ${}_{th},$

$($i$)$ the specific fuel consumption G $,$

$($j$)$ the overall efficiency ${}_0.$