Air at a stagnation temperature of $15^{\circ} \mathrm{C}$ and stagnation pressure $100 \mathrm{kPa}$ enters an axial compressor with an absolute velocity of $120 \mathrm{~m} / \mathrm{s}$. Inlet guide vanes direct this absolute velocity to the rotor inlet at an angle of $18^{\circ}$ to the axial direction. The rotor turning angle is $27^{\circ}$ and the mean blade speed is $200 \mathrm{~m} / \mathrm{s}$. The axial velocity is assumed constant through the stage.
The blade angle at the inlet of the rotor is
(A) $25.5^{\circ}$
(B) $38.5^{\circ}$
(C) $48.5^{\circ}$
(D) $59.5^{\circ}$
Air at a stagnation temperature of $15^{\circ} \mathrm{C}$ and stagnation pressure $100 \mathrm{kPa}$ enters an axial compressor with an absolute velocity of $120 \mathrm{~m} / \mathrm{s}$. Inlet guide vanes direct this absolute velocity to the rotor inlet at an angle of $18^{\circ}$ to the axial direction. The rotor turning angle is $27^{\circ}$ and the mean blade speed is $200 \mathrm{~m} / \mathrm{s}$. The axial velocity is assumed constant through the stage.
The blade angle at the inlet of the rotor is
(A) $25.5^{\circ}$
(B) $38.5^{\circ}$
(C) $48.5^{\circ}$
(D) $59.5^{\circ}$
(A) $25.5^{\circ}$
(B) $38.5^{\circ}$
(C) $48.5^{\circ}$
(D) $59.5^{\circ}$