The mass flow rate through the nozzle of a rocket engine is the amount of propellant expelled per unit of time, and it is a crucial parameter in understanding the engine’s performance.
you can express the mass flow rate through a nozzle for a Scramjet Engine 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).