Author name: Gurupriya Dey Sarkar

The total energy at the nozzle inlet for a turboprop engine involves considering the enthalpy and kinetic energy of the incoming air before combustion. Turboprop engines are a type of aircraft propulsion system that use a gas turbine engine to drive a propeller. This formula combines the static enthalpy, which represents the energy content of […]

This formula accounts for both the internal energy associated with the temperature and pressure of the incoming air (static enthalpy) and the energy associated with the motion of the air (kinetic energy). To use this formula, you would need specific values for the static enthalpy and the velocity of the incoming air. These values are

Calculating the total energy at the nozzle inlet for a turbojet engine involves considering the enthalpy and kinetic energy of the incoming air before combustion. The total energy (E) at the nozzle Inlet can be expressed as: where, E is the Total Energy, i.e sum of kinetic and potential energy h is the Static Enthalpy

Nuclear pulse engines are a theoretical type of propulsion system that envisions the use of nuclear explosions to generate thrust. This concept is often associated with interstellar spacecraft propulsion. In the context of a nuclear pulse engine, the “nozzle exit” refers to the point where the high-speed products of nuclear explosions are expelled. The total

Pulsed Detonation Engines (PDEs) are a type of propulsion system that operates on the detonation principle. They use a repetitive cycle of fuel injection, ignition, and detonation to generate thrust. In the context of a Pulsed Detonation Engine, the “nozzle exit” refers to the point where the high-speed combustion products exit the engine. The total

In the context of a methane rocket engine, the “nozzle exit” is the point where high-speed combustion products, including water vapor and carbon dioxide, exit the rocket nozzle. The total energy per unit mass at the nozzle exit can be expressed as the sum of the enthalpy and kinetic energy of the combustion products. The total

A hybrid-propellant rocket is a rocket with a rocket motor that uses rocket propellants in two different phases: one solid and the other either gas or liquid. In the context of a hybrid rocket engine, the “nozzle exit” refers to the point where the high-speed combustion products exit the rocket nozzle. Hybrid rocket engines use a

A Nuclear Thermal Rocket (NTR) engine is a type of rocket engine that uses nuclear reactions to heat a propellant, typically hydrogen, which is then expelled through a rocket nozzle to produce thrust. In the context of an NTR engine, the term “nozzle exit” refers to the point where the high-speed heated propellant is expelled.

The GE9X engine is a high-bypass turbofan jet engine developed by General Electric for use on large commercial aircraft, specifically the Boeing 777X. In the context of a turbofan engine like the GE9X, the term “nozzle exit” refers to the point where the high-speed exhaust gases exit the engine’s jet nozzle. The total energy at

Pulsejet engines are a type of air-breathing jet engine known for their simple design and intermittent combustion process. They operate on the principle of utilizing shock waves and pressure variations to generate thrust. Pulsejet engines don’t have a traditional nozzle exit like in turbojet or rocket engines, but the total energy at the exit can