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 rateĀ for a liquid propellant rocket engine is the rate at which the liquid propellants are expelled from the rocket nozzle during combustion.
Where:
- į¹ Ā is the mass flow rate (kg/s),
- is the density of the exhaust gases (kg/mĀ³),
- is the throat area of the rocket nozzle (mĀ²),
- is the effective exhaust velocity (m/s).