Mass flow through a rocket engine refers to the rate at which propellant material (usually a combination of fuel and oxidizer) is being consumed and expelled from the engine to produce thrust. In a rocket engine, propellant is burned in a combustion chamber to generate high-speed exhaust gases. These gases are expelled through a nozzle at the rear of the engine, creating a reactive force known as thrust that propels the rocket forward.
- Inlet pressure (p0) in N/m^2
- Cross-sectional area at sonic flow (A*) in m^2
- Inlet temperature (T0) in K
- Specific heat ratio (𝛾)
- Specific gas constant (R) in J/kg*K
- Mass flow rate (ṁ) in kg/s