Cryogenic rocket engines use cryogenic propellants, typically liquid oxygen (LOX) and liquid hydrogen (LH2), which are stored at extremely low temperatures. The thrust is generated by the combustion of these cryogenic propellants in the rocket engine.
If you have specific data on thrust, burn time, and the mass of cryogenic propellant consumed during the operation of a cryogenic rocket engine, you can use these formulas to calculate the specific impulse.
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