A jet fighter is flying at $\backslash (\backslash$mathcal$\{$M$\}=2\backslash )$ in still air that has $\backslash ($ T$=0^\{\backslash$circ$\}\backslash$mathrm$\{$F$\}\backslash )$ and $\backslash ($ P$=4\mathrm{.}0\backslash )$ psia. The air inlet to the jet engine is a converging$-$diverging diffuser. Inside the engine, the flow is subsonic. The area at the throat is $\backslash (2\mathrm{.}0\backslash$mathrm$\{$ft$\}^\{2\}\backslash ).$ What is the mass flow rate through the diffuser, assuming isentropic flow. It will be useful if you switch the frame of reference to have the jet stand still. $[167$ lbm$/$s$]$