GATE_AE_2027_MOCK_04_Q55
GATE 2027 Aerospace Engineering All-India Master Mock 04 (Aerospace Structures, Thin-Walled Beams & Aeroelasticity)
NAT · 2 Marks
Propulsion • Inlets, Combustors & Nozzles • Convergent-Divergent Nozzle & Choking
A de Laval rocket nozzle has throat area A_t = 0.04 m^2. If the exit Mach number is M_e = 3.0 and \gamma = 1.4, the area ratio A_e / A_t is given by isentropic relations as 4.2346. What is the required exit area A_e in m^2? (Round to three decimal places).
Answer Key:
0.169
Step-by-Step Verified Solution
### Solution: A_e = (A_e / A_t) * A_t = 4.2346 * 0.04 = 0.16938 ≈ 0.169 m^2. Correct: 0.169 (range 0.167 to 0.171).