GATE_AE_2027_MOCK_05_Q55 GATE 2027 Aerospace Engineering All-India Master Mock 05 (High-Yield Comprehensive Grand Finale) NAT · 2 Marks
Propulsion • Inlets, Combustors & Nozzles • Convergent-Divergent Nozzle & Choking

A rocket nozzle discharges hot gas (\gamma = 1.20) with total temperature T_0 = 3000 K. What is the static temperature T^* (in Kelvin) at the choked nozzle throat?

Answer Key:
2727

Step-by-Step Verified Solution

### Solution: T^* / T_0 = 2 / (\gamma + 1) = 2 / (1.20 + 1) = 2 / 2.20 = 1 / 1.10 = 0.90909... T^* = 3000 / 1.10 = 2727.27 K ≈ 2727 K. Correct: 2727 (range 2720 to 2735).
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