$9\mathrm{.}58$ WP Air at $\backslash (26\backslash$mathrm$\{$kPa$\},230\backslash$mathrm$\{$~K$\}\backslash ),$ and $\backslash (220\backslash$mathrm$\{$~m$\}/\backslash$mathrm$\{$s$\}\backslash )$ enters a turbojet engine in flight. The air mass flow rate is $\backslash (25\backslash$mathrm$\{$~kg$\}/\backslash$mathrm$\{$s$\}\backslash ).$ The compressor pressure ratio is $11,$ the turbine inlet temperature is $1400$ K $,$ and air exits the nozzle at $26$ kPa $.$ The diffuser and nozzle processes are isentropic$,$ the compressor and turbine have isentropic efficiencies of $\backslash (85\backslash \%\backslash )$ and $\backslash (90\backslash \%\backslash ),$ respectively, and there is no pressure drop for flow through the combustor. Kinetic energy is negligible everywhere except at the diffuser inlet and the nozzle exit. On the basis of air$-$standard analysis, determine

a$.$ the pressures, in kPa $,$ and temperatures, in K $,$ at each principal state.

b$.$ the rate of heat addition to the air passing through the combustor, in $\backslash (\backslash$mathrm$\{$kJ$\}/\backslash$mathrm$\{$s$\}\backslash ).$

c$.$ the velocity at the nozzle exit, in $\backslash (\backslash$mathrm$\{$m$\}/\backslash$mathrm$\{$s$\}\backslash ).$