The mass flow rate of air and fuel into a can-type combustion chamber in aircraft design represents the amount of air and fuel that are being mixed and burned. The formula to calculate the mass flow rate (ṁ) into the can-type combustion chamber is as follows:
- ṁ = Mass flow rate (in kilograms per second, kg/s)
- ρ = Density of the air-fuel mixture in the combustion chamber (in kilograms per cubic meter, kg/m³)
- A = Cross-sectional area of the combustion chamber inlet (in square meters, m²)
- V = Inlet velocity of the air-fuel mixture (in meters per second, m/s)