GATE_AE_2027_MOCK_03_Q58 GATE 2027 Aerospace Engineering All-India Master Mock 03 (Flight Dynamics, Controls & Space Trajectories) NAT · 2 Marks
Propulsion • Rocket Propulsion • Solid, Liquid & Hybrid Rocket Engines

A solid rocket propellant has a burning rate law r = a P_c^n with a = 3.0 mm/(s * MPa^n) and burning rate exponent n = 0.50. What is the linear burning rate r (in mm/s) at chamber pressure P_c = 4.0 MPa?

Answer Key:
6.0

Step-by-Step Verified Solution

### Solution: r = a * P_c^n = 3.0 * (4.0)^{0.50} = 3.0 * 2.0 = 6.0 mm/s. Correct: 6.0.
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