Liquid flyback booster rocket engines are designed to be part of a reusable launch system where the booster stage returns to Earth for recovery and reuse. These engines are typically used in the initial stage of a rocket launch.
To calculate the specific impulse for a specific liquid flyback booster rocket engine, you would need specific data on thrust, 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