Full-flow staged combustion engines represent a type of rocket engine design where both the fuel and oxidizer are fully combusted in separate combustion cycles, and the resulting hot gases are combined and expanded through a rocket nozzle to produce thrust.
To assess the specific impulse for a specific full-flow staged combustion engine, you would need information on the engine’s thrust output, burn time, and the total mass of propellant consumed during the burn. These values can be obtained from engine tests, simulations, or design specifications.
It is defined as the thrust generated per unit of propellant expended and is expressed in seconds.
where,
- is the specific impulse of the rocket engine (in seconds, s)
- F is the Thrust Produced
- ṁ is the mass flow rate of propellant in KG/Sec
- g0 is the acceleration due to gravity