In a liquid propellant rocket engine, the mass flow rate is determined by the rate at which the liquid propellants are pumped into the combustion chamber and subsequently expelled through the rocket nozzle.
The mass flow rate for a liquid propellant rocket engine is the rate at which the liquid propellants are expelled from the rocket nozzle during combustion.
you can express the mass flow rate through a nozzle for a Nozzle Mass Flow Rate For a Cold Gas Propulsion Rocket Engine In Terms of Ideal Gas Law and Isentropic Flow in Ideal Gas and Isentropic flow in terms of known parameters like pressures, temperatures, and throat area:
where,
- ṁ is the mass flow rate of the nozzle
- P is the pressure
- R is the gas constant for the working fluid
- T is the Temperature
- A is the throat nozzle area
- is the specific impulse of the engine (s),
- g0 is the acceleration due to gravity (approximately 9.81 m/s²).