Nozzle Mass Flow Rate For a Cold Gas Propulsion Rocket Engine In Terms of Ideal Gas Law 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 mass flow rate for a Cold Gas Propulsion rocket engine is the rate at which the combustion gases are expelled from the rocket nozzle due to the burning of the solid propellant.

The density ($\rho$) of the incoming air can be determined using the ideal gas law:

which gives,

where,

• ṁ is the mass flow rate (kg/s),​
• $P$ is the pressure of the incoming air (Pa),
• $R$ is the specific gas constant for air (J/(kg·K)),
• $T$ is the temperature of the incoming air (K).
• $A$ is the cross-sectional area of the nozzle (m²),
• $V$ is the velocity of the air through the nozzle (m/s).