Author name: Gurupriya Dey Sarkar

In a liquid propellant rocket engine, combustion occurs in a combustion chamber where liquid oxidizer and liquid fuel are injected, mixed, and then ignited. The combustion of liquid propellants results in the generation of hot gases that are expelled through a nozzle to produce thrust. The flame temperature in a liquid propellant rocket engine is […]

In a solid propellant rocket engine, combustion occurs in a confined space within the rocket motor, where a solid propellant undergoes combustion to produce hot gases that are expelled through a nozzle to generate thrust. The flame temperature in a solid propellant rocket engine is a crucial parameter influencing the engine’s performance. However, determining the

The flame temperature of combustion in a rocket engine refers to the temperature achieved during the combustion of propellant in the combustion chamber. Unlike air-breathing engines (like those on aircraft), rockets carry their own oxidizer and do not rely on atmospheric oxygen for combustion. The flame temperature in a rocket engine is a critical parameter

The flame temperature of combustion in a turboshaft engine, as in other types of aircraft engines, refers to the temperature reached during the combustion of fuel in the engine’s combustion chamber. The flame temperature is a crucial parameter influencing the engine’s efficiency, performance, and emissions. The adiabatic flame temperature Tadiabatic is an estimate of the maximum

The flame temperature of combustion in a turbofan engine, like in other types of aircraft engines, refers to the temperature reached during the combustion of fuel in the engine’s combustion chamber. The flame temperature is a critical parameter influencing the engine’s efficiency, performance, and emissions. The adiabatic flame temperature Tadiabatic is an estimate of the maximum

The flame temperature of combustion in a turbofan engine, like in other types of aircraft engines, refers to the temperature reached during the combustion of fuel in the engine’s combustion chamber. The flame temperature is a critical parameter influencing the engine’s efficiency, performance, and emissions. The actual flame temperature in real-world conditions may differ from

The flame temperature of combustion in an aircraft refers to the temperature achieved during the combustion of fuel in the aircraft’s engine. This temperature is a critical parameter because it affects the efficiency of the engine and influences the performance of the aircraft. The flame temperature depends on factors such as the type of fuel

The flame temperature of combustion in an aircraft refers to the temperature achieved during the combustion of fuel in the aircraft’s engine. This temperature is a critical parameter because it affects the efficiency of the engine and influences the performance of the aircraft. The flame temperature depends on factors such as the type of fuel

For a cold gas propulsion system, where a pressurized gas is expelled to generate thrust, the velocity of the exhaust gases at the nozzle exit can be calculated using a simplified form of the rocket equation. In the case of cold gas propulsion, the specific impulse (Isp​) is essentially the exit velocity of the gas.

The velocity of the exhaust gases at the nozzle exit for a liquid propellant rocket engine is determined by the rocket equation, which is based on the conservation of momentum and mass. The rocket equation is universally applicable to different types of rocket engines, including liquid propellant engines. Liquid propellant engines use liquid fuels and