# 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

3537

(D) 157

Next Question :

A cryogenic rocket has a specific impulse of $455 s$ and characteristic velocity of $2386 \mathrm{~m} / \mathrm{s}$. The value of thrust coefficient for this rocket is
(A) 1.78
(B) 1.73
(C) 1.87
(D) 1.95 