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

In a cold gas propulsion rocket engine, the propulsion is achieved by expelling a compressed gas, typically at ambient temperature, to generate thrust. These systems are often used in small-scale applications, such as attitude control for spacecraft. The mass flow rate for a cold gas rocket engine is determined by the rate at which the compressed gas is expelled.

The mass flow rate for a cold gas propulsion rocket engine is the rate at which the compressed gas is expelled from the rocket nozzle to generate thrust.

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 Rocket 
• g₀ is the acceleration due to gravity (approximately 9.81 m/s² for Earth).