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 rateĀ 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 mass flow rate for a solid rocket engine can be approximated as:
Where:
- į¹ is the mass flow rate (kg/s),
- Ā is the density of the air (kg/mĀ³),
- Ā is the cross-sectional area of the nozzle (mĀ²),
- Ā is the velocity of the air through the nozzle (m/s).