Example $7-4.$ Let's consider another example in which we let the Mach number vary and see how the engine performance changes. The flight conditions, design limits$,$ component performance figures of merit, and design choices are listed below. We will compare the turbojet engine with losses with the corresponding ideal engine. The trends that were obtained for the ideal engine are generally true for the engine with losses; exceptions are noted in the following discussion.

INPUTS:

$M_0=14,T_0=216\mathrm{.}7K,{}_c=1\mathrm{.}4,c_{pc}=1\mathrm{.}004k\frac{J}{kg*K},{}_t=1\mathrm{.}35,$

$c_{pt}=1\mathrm{.}096k\frac{J}{kg*K},h_{PR}=42,800k\frac{J}{k}g,{}_{\text{d}\text{m}\text{a}\text{x}}=0\mathrm{.}98,{}_b=0\mathrm{.}98,$

${}_n=0\mathrm{.}96,e_c=0\mathrm{.}89,e_t=0\mathrm{.}91,{}_b=0\mathrm{.}99,{}_m=0\mathrm{.}98,\frac{P_0}{P_9}=1,T_{t4}=$

$1670K,{}_c=8$ and $24$