In aircraft design, the mass flow rate through a pressure injection carburetor 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 of the carburetor inlet (in square meters, m²)
– ρ is the air density at the carburetor inlet (in kilograms per cubic meter, kg/m³)
– V is the velocity of the air entering the carburetor (in meters per second, m/s)