Author name: Gurupriya Dey Sarkar

The throat of a rocket nozzle is a critical part of its design, representing the narrowest section through which the high-speed exhaust gases pass. The throat is where the flow velocity reaches its maximum value. The design of the throat is crucial for controlling the flow of exhaust gases and optimizing the expansion of the […]

The design of the inlet for a scramjet engine is a critical aspect of optimizing its performance. Scramjets (supersonic combustion ramjet) operate at hypersonic speeds and rely on efficient air intake and compression for proper combustion. The inlet is designed to slow down and compress the incoming supersonic airflow, preparing it for combustion within the

The design of the inlet for a ramjet engine is a critical aspect of optimizing its performance. Ramjets operate at supersonic speeds and rely on efficient air intake to achieve combustion. The inlet is designed to slow down and compress the incoming supersonic airflow, preparing it for combustion within the engine. The cross-sectional area of

In a turboprop engine, the nozzle is designed to accelerate and direct the exhaust gases rearward to generate thrust and also to provide a smooth exit for the propeller’s airflow. The design of the inlet for a turboprop engine is a crucial aspect of optimizing its performance. Turboprop engines use a combination of a gas

The design of the inlet for a turbofan engine is a critical aspect of optimizing its performance. Turbofan engines are a type of air-breathing jet engine that feature a large fan at the front, which helps compress air and enhances overall efficiency. The inlet is designed to efficiently channel air into the engine for combustion.

The design of the inlet for a turbojet engine is a critical aspect of optimizing its performance. Turbojet engines are air-breathing jet engines that compress air, mix it with fuel, combust it, and then expel the exhaust gases to generate thrust. The cross-sectional area of the inlet is an important parameter, and it is typically

The total energy at the nozzle inlet of a rocket is the sum of the kinetic energy and specific enthalpy of the propellant (fuel and oxidizer) per unit mass before it undergoes combustion and expansion in the rocket engine. In the context of rocket propulsion, this energy is often expressed in terms of specific energy,

The total energy at the nozzle inlet of a rocket is the sum of the kinetic energy and specific enthalpy of the propellant (fuel and oxidizer) per unit mass before it undergoes combustion and expansion in the rocket engine. In the context of rocket propulsion, this energy is often expressed in terms of specific energy,

The total energy at the nozzle inlet of a rocket is the sum of the kinetic energy and specific enthalpy of the propellant (fuel and oxidizer) per unit mass before it undergoes combustion and expansion in the rocket engine. The total energy (E) at the nozzle exit can be expressed as: where, E is the

The total energy at the nozzle inlet of a rocket is the sum of the kinetic energy and specific enthalpy of the propellant (fuel and oxidizer) per unit mass before it undergoes combustion and expansion in the rocket engine. The total energy (E) at the nozzle exit can be expressed as: where, E is the