Author name: Gurupriya Dey Sarkar

the Rolls-Royce Gnome is a turboshaft engine, commonly used in helicopters. The thermal efficiency of a turboshaft engine is a measure of how effectively the engine converts the chemical energy in fuel into useful work, typically in the form of shaft power. The thermal efficiency is defined as the ratio of the useful work output […]

The thermal efficiency of an aircraft piston engine is a measure of how effectively the engine converts the chemical energy in fuel into useful work. Piston engines, also known as reciprocating engines, are commonly used in smaller aircraft. The thermal efficiency is defined as the ratio of the useful work output to the energy input from

The thermal efficiency of a high bypass ratio (HBR) turbofan engine is a measure of how effectively the engine converts the chemical energy in fuel into useful work, primarily in the form of thrust. High bypass ratio turbofan engines are designed with a significant portion of the incoming air bypassing the combustion process, resulting in

The thermal efficiency of a turboshaft engine is a measure of how effectively the engine converts the chemical energy in fuel into useful work, typically in the form of shaft power. Turboshaft engines are commonly used to power helicopters and other rotorcraft, providing the mechanical power needed to turn the rotor. The thermal efficiency is

The thermal efficiency of a turboprop engine is a measure of how effectively the engine converts the chemical energy in fuel into useful work, typically measured in terms of the propeller thrust and/or shaft power. The thermal efficiency is defined as the ratio of the useful work output to the energy input from burning the

he thermal efficiency of a turbofan engine is a measure of how effectively the engine converts the chemical energy in fuel into useful work, typically measured in terms of thrust. It is defined as the ratio of the useful work output (thrust) to the energy input from burning the fuel. In a turbofan engine, a

The thermal efficiency ηth of a turbojet engine is a measure of how effectively it converts the chemical energy in fuel into useful work in the form of thrust. It is defined as the ratio of the useful work output (thrust) to the energy input from burning the fuel. The thermal efficiency is a crucial parameter

The propulsive efficiency of a hypergolic bipropellant rocket engine can be calculated similarly to the general case mentioned earlier. Hypergolic propellants are those that ignite spontaneously upon contact with each other, eliminating the need for an external ignition source. A bipropellant system uses two separate components, typically a fuel and an oxidizer, which are mixed

The propulsive efficiency of a rocket engine that uses methane (CH₄) as fuel and liquid oxygen (O₂) as oxidizer, often referred to as a “methalox” engine, can be calculated similarly to the general case explained earlier. The propulsive efficiency is a crucial parameter in evaluating the performance of a rocket engine, indicating how well it

A dual-mode rocket engine typically refers to an engine that can operate in two different modes, such as liquid and solid propellants, or different combustion processes for different phases of the mission. The propulsive efficiency is a crucial parameter in evaluating the performance of a rocket engine, indicating how well it converts propellant energy into