# An axial compressor that generates a stagnation pressure ratio of 4.0 , operates with inlet and exit stagnation temperatures of $300 \mathrm{~K}$ and $480 \mathrm{~K}$, respectively. If the ratio of specific heats $(\gamma)$ is $1.4,$ the isentropic efficiency of the compressor is (A) 0.94 (B) 0.81 (C) 0.72 (D) 0.63

## Question ID - 155528 :- An axial compressor that generates a stagnation pressure ratio of 4.0 , operates with inlet and exit stagnation temperatures of $300 \mathrm{~K}$ and $480 \mathrm{~K}$, respectively. If the ratio of specific heats $(\gamma)$ is $1.4,$ the isentropic efficiency of the compressor is (A) 0.94 (B) 0.81 (C) 0.72 (D) 0.63

3537

(B) 0.81

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A rocket has an initial mass of $150 \mathrm{~kg}$. After operating for a duration of $10 \mathrm{~s}$, its final mass is $50 \mathrm{~kg}$. If the acceleration due to gravity is $9.81 \mathrm{~m} / \mathrm{s}^{2}$ and the thrust produced by the rocket is $19.62 \mathrm{kN}$, the specific impulse of the rocket is
(A) $400 \mathrm{~s}$
(B) $300 \mathrm{~s}$
(C) $200 \mathrm{~s}$
(D) $100 \mathrm{~s}$