Nozzle Mass Flow Rate For a Liquid Propellent Rocket Engine In Nozzle Mass Flow Rate For a Liquid Propellent Rocket Engine In Terms of Isentropic Flow Calculator

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.

The velocity ($V$) in terms of the local speed of sound ($a$) is given by:

which gives,

where,

• ṁ is the mass flow rate of the nozzle
• At​ is the throat area of the rocket nozzle (m²),
• I_sp is the Specific Impulse of the Rocket
• g₀ is the acceleration due to gravity (approximately 9.81 m/s² for Earth).