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.
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