Nozzle Mass Flow Rate For a Solid Propellent Rocket Engine In Terms of Ideal Gas Law Calculator

In a solid propellant rocket engine, the mass flow rate is determined by the rate at which the solid propellant is burned and expelled. Unlike liquid or gaseous propellants, the mass flow rate in solid rocket engines is not easily adjustable during operation.

The mass flow rate for a solid propellant 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).