Consider the design of turbojet engine intended to produce a thrust of 111 kN at a takeoff velocity of 66 m/s at sea level. At takeoff, the gas velocity at the exit of the engine (relative to the engine) is 510 m/s. The fuel-air ratio by mass is 0.03. The exit pressure is equal to the ambient pressure. Calculate the area of the inlet to the engine necessary to obtain this thrust. $T = (dot{m}_{air} + dot{m}_{fuel}) V_j - dot{m}_{air} V_{infty} + (p_e - p_{infty}) A_e$
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First, we need to find the mass flow rate (m_dot) of the air through the engine. We can use the thrust equation: Thrust = m_dot * (V_exit - V_ambient) + (P_exit - P_ambient) * A_exit where Thrust = 11,000 N (given) V_exit = 510 m/s (given) V_ambient = 66 m/s Show moreā¦
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A pure jet engine propels an aircraft at $240 \mathrm{~m} / \mathrm{s}$ through air at $45 \mathrm{kPa}$ and $-13^{\circ} \mathrm{C}$. The inlet diameter of this engine is $1.6 \mathrm{~m},$ the compressor pressure ratio is $13,$ and the temperature at the turbine inlet is $557^{\circ} \mathrm{C}$. Determine the velocity at the exit of this engine's nozzle and the thrust produced. Assume ideal operation for all components and constant specific heats at room temperature.
A pure jet engine propels an aircraft at $240 \mathrm{m} / \mathrm{s}$ through air at $45 \mathrm{kPa}$ and $-13^{\circ} \mathrm{C}$. The inlet diameter of this engine is $1.6 \mathrm{m},$ the compressor pressure ratio is $13,$ and the temperature at the turbine inlet is $557^{\circ} \mathrm{C}$. Determine the velocity at the exit of this engine's nozzle and the thrust produced. Assume ideal operation for all components and constant specific heats at room temperature.
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