The mass flow rate (ṁ) of air through an airplane turbine engine can be calculated using the following formula:
- ṁ is the mass flow rate in kilograms per second (kg/s).
- A is the cross-sectional area through which air is ingested into the engine in square meters (m²).
- V is the velocity of the air entering the engine in meters per second (m/s).
- ρ is the density of the air in kilograms per cubic meter (kg/m³).