Thermodynamic calculation of turbofan engine with afterburner

Givens:

Flight conditions: $M=1\mathrm{.}2$;$H=5$

Required thrust: $F=150000N$

Main working process parameters:

${}_{0e}=13$;$T_{03}=1700K$;$=0\mathrm{.}25$;${}_{0F}=1\mathrm{.}2$;$T_{0\frac{}{b}}=2100K$

Coefficients and other givens:

Perform the following:

Draw the schematic diagram of the given engine with appropriate

station numbering and the corresponding thermodynamic cycle in $p-v$

and T$-$S coordinate systems

Calculate all the thermodynamic parameters at each station of the

engine including the critical parameters of the jet nozzle $($ that is to

mean: total and static pressures, total and static temperatures, total

compression ratio, jet nozzle pressure ratio, jet nozzle critical

pressure ratio, jet nozzle critical temperature and pressure and other

parameters that can be used as an input to determine engine main and

working process parameters$)$

Calculate $F_{sp},f_{sp},m_a^{}$ and cross sectional area of the inlet section and

the jet nozzle section

Calculate the engine useful cyclic work, engine thermal, propulsive

and overall efficiencies

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