Component Efficiencies: A compressor is tested on a static test stand at standard sea level

conditions $(p_a=101,325Pa,T_a=288\mathrm{.}15K)$; at these conditions, you may assume an ideal

gas with constant $=1\mathrm{.}4.$ The test article includes an inlet upstream of the compressor,

with sensors to measure stagnation pressure the compressor inlet and stagnation pressure and

stagnation temperature at the compressor exit. When run at its design speed, the measured

compressor inlet stagnation pressure is $p_{02}=100$kPa and the measured compressor exit

conditions are $p_{03}=4\mathrm{.}00$MPa,$T_{03}=922K.$

$($a$)$ What is inlet stagnation pressure ratio, $r_d?$ Why is inlet adiabatic efficiency not a useful

performance metric in this circumstance?

$($b$)$ What is the compressor adiabatic efficiency?

$($c$)$ Sketch a $T-$s diagram of the flow processes through the inlet and compressor. Be sure to

indicate points that represents ambient conditions $($a$),$ compressor inlet stagnation con$-$

ditions $(02),$ and compressor exit stagnation conditions $(03),$ and isobars for pressures

$p_a,p_{02},$ and $p_{03}.$