List of top Propulsion Questions on Thrust equation and specific impulse asked in GATE AE

An ideal rocket has characteristic exhaust velocity of 1200 m/s, mass flow rate of 75 kg/s, thrust coefficient of 1.5, and nozzle throat area of 0.025 \(\text{m}^2\). The chamber pressure in kPa and the specific impulse due to gravity in seconds are ________, respectively. Assume that the acceleration due to gravity is 9.8 \(\text{m/s}^2\).

Consider a launch vehicle of mass 10 tons being launched vertically. The vehicle has 8 tons of propellant, which burns completely at a constant rate over 50 s. If the engine specific impulse is 250 s, and the acceleration due to gravity at sea level is \(g_0\), the acceleration experienced by the vehicle at lift-off is ________.

Hot gases at 2100 K and 14 MPa expand ideally to 0.1 MPa through a rocket nozzle.
Molecular mass = 22 kg/kmol, heat-capacity ratio $\gamma = 1.32$,
Universal gas constant = 8314 J/kmol-K, \(g = 9.8\,\text{m/s}^2\).
Throat area = \(0.1\ \text{m}^2\). Find the specific impulse (round off to 2 decimals).