8.8
The absolute flow angle at the inlet of a stator blade in
a compressor is $\alpha_2 = 45^\circ$, as shown. The absolute total pres-
sure and temperature in station 2 are $p_{t2} = 150 \text{ kPa}$ and $T_2$
$= 300 \text{ K}$, respectively. The total pressure loss coefficient for
this section of the stator blade is $\omega_s = 0.02$. Assuming the
axial velocity remains constant and gas properties are $\gamma = 1.4$
and $c_p = 1.004 \text{ kJ/kg} \cdot \text{K}$, calculate
(a) entrance Mach number $M_2$
(b) exit total pressure $p_{t3}$
(c) exit Mach number $M_3$
(d) static pressure rise, $\Delta p = p_3 - p_2$
