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.
you can express the mass flow rate through a nozzle for a Nozzle Mass Flow Rate For a Solid Propellent Rocket Engine In Terms of Ideal Gas Law and Isentropic Flow in Ideal Gas and Isentropic flow in terms of known parameters like pressures, temperatures, and throat area:
where,
- ṁ is the mass flow rate of the nozzle
- P is the pressure
- R is the gas constant for the working fluid
- T is the Temperature
- A is the throat nozzle area
- is the specific impulse of the engine (s),
- g0 is the acceleration due to gravity (approximately 9.81 m/s²).