$10\mathrm{.}4$ A turbine stage is designed with a constant axial velocity of $250\frac{m}{s}$ and zero exit swirl. For a rotor rotational speed $U_m$ at the pitchline of $600\frac{m}{s}.$

Calculate:

a$.$ the nozzle exit flow angle, ${}_2$ in degrees for $R_m=0\mathrm{.}50$

b$.$ the nozzle exit flow angle, ${}_2$ in degrees for $R_m=0\mathrm{.}0$

c$.$ the rotor specific work at the pitchline radius, for $R_m=0\mathrm{.}50$ and $R_m=0\mathrm{.}0$

Please solve all the parts with steps $!!!$