The mass flow rate ṁ 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. The formula for mass flow rate through a nozzle is given by:
where,
- ṁ is the mass flow rate of the nozzle
- is the density of the air (kg/m³),
- is the cross-sectional area of the nozzle (m²),
- is the velocity of the air through the nozzle (m/s).