GATE_AE_2027_MOCK_03_Q30
GATE 2027 Aerospace Engineering All-India Master Mock 03 (Flight Dynamics, Controls & Space Trajectories)
NAT · 1 Mark
Propulsion • Rocket Propulsion • Rocket Thrust, Specific Impulse & Characteristic Velocity
A solid rocket motor has throat area A_t = 0.02 m^2 and chamber pressure P_c = 5.0 MPa. If the characteristic velocity is c^* = 1500 m/s, what is the propellant mass flow rate \dot{m} in kg/s?
Answer Key:
66.67
Step-by-Step Verified Solution
### Solution: \dot{m} = (P_c * A_t) / c^* = (5.0 * 10^6 * 0.02) / 1500 = 100000 / 1500 = 66.67 kg/s. Correct: 66.67 (range 66.0 to 67.0).