Nozzle Mass Flow Rate For a Rocket Engine in Terms of Isentropic Flow Calculator

The mass flow rate through the nozzle of a rocket engine is the amount of propellant expelled per unit of time, and it is a crucial parameter in understanding the engine’s performance.

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
• $\rho$ is the density of the exhaust gases at the throat
• A is the throat nozzle area
• I_sp​ is the specific impulse of the engine (s),
• g₀​ is the acceleration due to gravity (approximately 9.81 m/s²).