Problem No$.$ Points$)$

For the non$-$mixed turbofan engine shown below with the following assumptions:

Diffuser efficiency

Compressor efficiency

Fan efficiency

@ $100\%$

Turbine efficiency

@ $87\%$

Gas generator nozzle efficiency

@ $85\%$

Fan nozzle efficiency

@ $89\%$

@ $100\%$

Air mass flow rate thru only the fan

@ $100\%$

Air mass flow rate thru gas generator

@ $511$ lbs$./$s

Compressor pressure ratio

$(82lb\frac{s}{s}$

Fan pressure ration

@ $26\mathrm{.}6$

Turbine inlet stagnation temperature

@ $1\mathrm{.}64$

$($@$)2560$deg.$R$

All efficiencies are based on stagnation conditions.

At cruising speed with $Ma=0\mathrm{.}85$ @ $35,000$ feet, assuming air standard cycle with variable air properties, taking into account the ideal mass of the fuel$/$air flow added as $0\mathrm{.}0206,$ Find:

$($a$)$ The thrust developed by this engine and $\%$ of thrust from fan section.

$($b$)$ The thrust specific fuel consumption.