An aircraft is flying at Mach 3.0 at an altitude where the ambient pressure and temperature are 50 $k P a$ and $200 K$ respectively. If the converging-diverging diffuser of the engine (considered isentropic with ratio of specific heats, $\gamma=1.4$ and specific gas constant $\mathrm{R}=287 \mathrm{~J} / \mathrm{kgK}$ ) has a throat area of $0.05 \mathrm{~m}^{2},$ the mass flow rate through the engine in $\mathrm{kg} / \mathrm{s}$ is
(A) 197
(B) 232
(C) 790
(D) 157

Question ID - 155927 :-

An aircraft is flying at Mach 3.0 at an altitude where the ambient pressure and temperature are 50 $k P a$ and $200 K$ respectively. If the converging-diverging diffuser of the engine (considered isentropic with ratio of specific heats, $\gamma=1.4$ and specific gas constant $\mathrm{R}=287 \mathrm{~J} / \mathrm{kgK}$ ) has a throat area of $0.05 \mathrm{~m}^{2},$ the mass flow rate through the engine in $\mathrm{kg} / \mathrm{s}$ is
(A) 197
(B) 232
(C) 790
(D) 157

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