$3\mathrm{.}2$ Extending the example on the turbofan in Chapter $3,$ with the additional information that the combustion efficiency is $0\mathrm{.}99,$ determine the $SFC.$ Also, calculate the thrust and $SFC$ when a combustion chamber is incorporated in the bypass duct and the 'cold' stream is heated to $1000$ K $.$ The combustion efficiency and pressure loss for this process may be assumed to be $0\mathrm{.}97$ and $0\mathrm{.}05$ bar respectively.

$[0\mathrm{.}0429k\frac{g}{h}N$; $55\mathrm{.}95kN,0\mathrm{.}128k\frac{g}{h}N]$