A blade pair in an axial flow compressor is designed to achieve a stagnation temperature rise of $24K.$ At design, the mean blade speed is

$263\frac{m}{s}$ and the axial flow component of gas velocity is $180\frac{m}{s}.$ The relative flow angle at the rotor inlet is $45$ degrees. The engine diameter at

the mean blade height is $0\mathrm{.}8m$ and the blade height at rotor inlet is $0\mathrm{.}2m.$ The stagnation conditions at the inlet to the blade pair are $300K$ and

$130k\frac{N}{m^{{?}^{{?}^{?}}}}2.$ Calculate and comment on the following:

relative flow angle at exit from the rotor blades

absolute flow angles at inlet to and exit from stator

degree of reaction

air mass flow rate

given C$\_$p$=1\mathrm{.}005$ kJ$/$kg$/$K and $R=0\mathrm{.}287k\frac{J}{k}\frac{g}{K}.$