Author name: Gurupriya Dey Sarkar

you can analyze the energy transfer in terms of kinetic energy and enthalpy changes during the combustion and expansion processes. 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 energy (E) at the nozzle Inlet can be […]

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 a hybrid rocket engine, the combustion process typically involves a liquid oxidizer and a solid fuel. The combustion occurs at the interface between the liquid oxidizer and the

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. Nuclear thermal rocket engines operate on a fundamentally different principle compared to chemical rocket engines. In a nuclear thermal rocket engine, the

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

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

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 Inlet like in turbojet or rocket engines, but the total energy at the exit can

Rotary engines, often referred to as Wankel engines, are a type of internal combustion engine known for their unique rotor-based design. Unlike traditional piston engines, rotary engines have a rotating triangular rotor that completes three strokes (intake, compression, and exhaust) during one revolution. The exit of the exhaust gases in a rotary engine is not

piston engine is commonly found in internal combustion engines like those in cars or small aircraft. The total energy at the exit of a piston engine can be considered in terms of the kinetic energy of the exhaust gases as they leave the exhaust manifold. While it’s not as formally defined as in jet or

Propeller-driven engines, on the other hand, are a type of aircraft propulsion system that relies on the rotation of a propeller to generate thrust. For propeller-driven engines, the emphasis is on the aerodynamics of the propeller and the mechanical power it extracts from the engine to accelerate the air. The total energy (E) at the

The calculation of total energy at the nozzle inlet for an aerospike engine involves considering the enthalpy and kinetic energy of the propellants or combustion products before entering the nozzle. Aerospike engines are unique in design and feature a bell-shaped nozzle with an annular shape, providing thrust vectoring benefits. The specific values for these parameters