Author name: Gurupriya Dey Sarkar

The RD-170 is a liquid rocket engine developed in Russia. To calculate the specific impulse for the RD-170 engine, we need specific information about the engine’s thrust, and mass of propellant. For the RD-170 engine, you would need specific data from its operational parameters or historical records of its launches to plug into this formula. […]

The Saturn V rocket used a combination of liquid rocket engines for its first and second stages. Specifically, the first stage used five F-1 engines, and the second stage used five J-2 engines. To calculate the specific impulse for these engines, we need more specific information about the thrust, burn time, and mass of propellant.

Specific Impulse for a cold gas propulsion rocket nozzle is a parameter that measures the efficiency with which a rocket engine using cold gas as a propellant converts that propellant into thrust. Cold gas propulsion systems typically use compressed gas, often stored at ambient temperature, for thrust generation. Specific Impulse provides a metric for comparing

Specific Impulse for a liquid propellant rocket nozzle is a crucial performance parameter that quantifies the efficiency with which a liquid rocket engine converts propellant into thrust. It measures the impulse (thrust multiplied by time) produced per unit mass of propellant expended, providing a key metric for comparing rocket engines. The specific impulse of a

Specific Impulse for a solid propellant rocket nozzle is a measure of the efficiency with which a solid rocket motor converts its propellant into thrust. It quantifies the impulse (thrust multiplied by time) produced per unit mass of propellant expended. Specific Impulse is a crucial parameter in rocketry as it reflects the performance of the

The specific impulse for a turboshaft engine is sometimes used as a performance metric. This parameter is analogous to specific impulse but is more relevant for air-breathing engines like turboshafts. Specific impulse is more commonly used for rocket engines, where the combustion involves both fuel and oxidizer carried on board, whereas turboshafts draw in air

The specific impulse for a turbojet engine is sometimes used as a performance metric. This parameter is analogous to specific impulse but is more relevant for air-breathing engines like turbojets. Specific impulse is more commonly used for rocket engines, where the combustion involves both fuel and oxidizer carried on board, whereas turbojets draw in air

The specific impulse for a turboprop engine is sometimes used as a performance metric. This parameter is analogous to specific impulse but is more relevant for air-breathing engines like turboprops. Specific impulse is more commonly used for rocket engines, where the combustion involves both fuel and oxidizer carried on board, whereas turboprops draw in air

The specific impulse for a turbofan engine is sometimes used as a performance metric. This parameter is analogous to specific impulse but is more relevant for air-breathing engines like turbofans. Specific impulse is more commonly used for rocket engines, where the combustion involves both fuel and oxidizer carried on board, whereas turbofans draw in air

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. 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