Author name: Gurupriya Dey Sarkar

In a liquid propellant rocket engine, the nozzle exit is a critical point where the high-speed exhaust gases exit the rocket nozzle into space. The total energy at the nozzle exit is the sum of the enthalpy and kinetic energy of the exhaust gases. The total energy (E) at the nozzle exit can be expressed […]

Solid rocket engines typically use a grain of solid propellant that burns from the inside out, and the burning of the propellant occurs at the exposed surface of the grain. It’s important to note that for solid rocket engines, the specific details of the combustion process and the determination of internal energy depend on the

In the context of a rocket engine, the term “nozzle exit” typically refers to the point at which the high-speed exhaust gases exit the rocket nozzle into space. The total energy at the nozzle exit for a rocket engine is the sum of the enthalpy and kinetic energy of the exhaust gases. The static enthalpy includes

In a turboshaft engine, the nozzle exit typically refers to the exit of the gas turbine section, where the combustion gases pass through the power turbine before being used to drive a mechanical output, such as a helicopter rotor or industrial machinery. The static enthalpy includes the internal energy, pressure energy, and potential energy of the

In a turboprop engine, the nozzle exit refers to the exit of the gas turbine section, where the combustion gases pass through the power turbine before entering the propeller. The total energy at the nozzle exit is the sum of the enthalpy and kinetic energy of the exhaust gases. The total energy (E) at the

The total energy at the exit of a nozzle for a turbofan engine, similar to other propulsion systems, is a combination of enthalpy and kinetic energy. In the context of a turbofan engine, the nozzle exit refers to the exit of the nozzle guide vanes or stators, just before the gases enter the jet nozzle.

The total energy at the exit of a nozzle for a turbojet engine consists of kinetic energy and potential energy. The total energy per unit mass is the sum of the enthalpy and kinetic energy at the exit of the nozzle. The total energy (E) at the nozzle exit can be expressed as: where, E

The propulsive efficiency of a chemical rocket engine is a measure of how effectively the engine converts the chemical energy stored in its propellants into kinetic energy of the exhaust gases, ultimately producing thrust. The propulsive efficiency is typically expressed in terms of the effective exhaust velocity and the specific impulse. The specific impulse is

Hybrid rockets are a type of rocket propulsion system that combines features of both solid rocket engines and liquid rocket engines. In a hybrid rocket, one of the propellants is in solid form, typically a solid fuel, while the other propellant is in liquid or gaseous form, acting as the oxidizer. The propulsive efficiency of

The propulsive efficiency of a nuclear thermal rocket engine can be expressed in terms of the effective exhaust velocity and the specific impulse. Nuclear thermal rockets use the heat produced by a nuclear reactor to heat a propellant (such as hydrogen) to high temperatures, which is then expelled through a rocket nozzle to generate thrust.