Problem $2$:

Consider an ideal cycle ramjet $(p_4=p_0,{}_d=1,{}_b=1,{}_n=1).$ Given:

Flight conditions: $M_0=2,T_0=210K,P_0=30000Pa$

Fuel to air ratio: $f=0\mathrm{.}02$

Fuel heat content: $h=4\mathrm{.}3**{10}^7\frac{J}{K}g$

Air properties: $C_p=1004\frac{J}{Kg}.K,=1\mathrm{.}4$

Nozzle momentum flux: $m^{}{u}_4=10000kg*\frac{m}{se{c}^2}$

Determine:

$2\mathrm{.}1$ Ramjet mass flow rate

$2\mathrm{.}2$ Ramjet thrust