Air enters a turbojet engine at 260 m / s at a rate of 30 kg / s, and exits at 800 m / s relat

step 1 First writing V inlet is equal to 320 meter per second and V exit is equal to 650 meter per seco

Air enters a turbojet engine at 260 m / s at a rate of 30...

Air enters a turbojet engine at $260 \mathrm{~m} / \mathrm{s}$ at a rate of 30 $\mathrm{kg} / \mathrm{s}$, and exits at $800 \mathrm{~m} / \mathrm{s}$ relative to the aircraft. The thrust developed by the engine is (a) $8 \mathrm{kN}$ (b) $16 \mathrm{kN}$ (c) $24 \mathrm{kN}$ (d) $20 \mathrm{kN}$ (e) $32 \mathrm{kN}$

Air enters a turbojet engine at $260 \mathrm{~m} / \mathrm{s}$ at a rate of 30 $\mathrm{kg} / \mathrm{s}$, and exits at $800 \mathrm{~m} / \mathrm{s}$ relative to the aircraft. The thrust developed by the engine is
(a) $8 \mathrm{kN}$
(b) $16 \mathrm{kN}$
(c) $24 \mathrm{kN}$
(d) $20 \mathrm{kN}$
(e) $32 \mathrm{kN}$

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Key Concepts

Thrust Calculation

Thrust calculation involves quantifying the force produced by the engine based on the mass flow rate and the change in velocity of the fluid. This is achieved by multiplying the mass flow rate by the difference between the exit velocity and the entry velocity of the air.

Mass Flow Rate

Mass flow rate is a measure of the mass of fluid passing through a given cross-sectional area per unit time. It is a critical quantity in engine performance as it helps determine how much momentum is being carried by the fluid before and after energy is added to the system.

Momentum Conservation

Momentum conservation is a principle stating that in a closed system, the total momentum remains constant unless acted upon by external forces. When applied to jet engines, the change in momentum of the air stream as it accelerates through the engine is directly related to the thrust produced.

Newton's Second Law for Fluids

This concept applies Newton's second law to a continuous flow of fluid, indicating that the force exerted by a system is equal to the rate of change of momentum. In the context of engines, it is used to determine thrust by calculating the product of the mass flow rate and the change in velocity of the fluid.

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