GATE_AE_2027_MOCK_02_Q27 GATE 2027 Aerospace Engineering All-India Master Mock 02 (Compressible Aerodynamics & High-Speed Propulsion) NAT · 1 Mark
Propulsion • Thermodynamic Cycles of Gas Turbines • Turbojet and Turbofan Performance

A turbojet engine ingests air at mass flow rate $\dot{m}_a = 50\text{ kg/s}$ at flight velocity $u_0 = 200\text{ m/s}$. The exhaust jet velocity is $u_e = 600\text{ m/s}$. Neglecting fuel mass flow and pressure mismatch at nozzle exit, what is the net thrust generated in kilonewtons (kN)?

Answer Key:
20

Step-by-Step Verified Solution

### Solution: Thrust $F = \dot{m}_a (u_e - u_0) = 50 \times (600 - 200) = 50 \times 400 = 20000\text{ N} = 20\text{ kN}$. Correct: 20.
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