GATE_AE_2027_MOCK_05_Q42 GATE 2027 Aerospace Engineering All-India Master Mock 05 (High-Yield Comprehensive Grand Finale) NAT · 2 Marks
Aerodynamics & Fluid Mechanics • Compressible Flow & Shocks • Normal & Oblique Shock Waves

A supersonic flow at Mach M_1 = 2.40 passes through a normal shock wave. If static temperature upstream is T_1 = 220 K, what is the downstream static temperature T_2 in Kelvin? (\gamma = 1.4, given T_2 / T_1 = 2.040, round to one decimal place).

Answer Key:
448.8

Step-by-Step Verified Solution

### Solution: T_2 = 2.040 * T_1 = 2.040 * 220 = 448.8 K. Correct: 448.8 (range 446.0 to 452.0).
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