The nozzle mass flow, also known as the mass flow rate through a rocket nozzle, is a crucial parameter in rocket propulsion systems. It represents the rate at which propellant mass is expelled from the rocket engine’s combustion chamber and out through the nozzle. This mass flow rate is directly related to the thrust produced by the rocket.
The nozzle mass flow rate (ṁ, pronounced as “m-dot”) is calculated using the following equation in SI units:
Where:
- ṁ is the nozzle mass flow rate (in kilograms per second, kg/s).
- is the throat area of the nozzle (in square meters, m²).
- is the density of the exhaust gases at the throat (in kilograms per cubic meter, kg/m³).
- is the exhaust velocity (in meters per second, m/s).