The mass flow rate of fuel and air into a combustion chamber in aircraft design is a critical parameter that represents the amount of air and fuel being mixed and burned. The formula to calculate the mass flow rate (ṁ) into the combustion chamber is as follows:
- ṁ = Mass flow rate (in kilograms per second, kg/s)
- ρ = Density of the mixture (a combination of air and fuel) 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 mixture (in meters per second, m/s)