The cross-sectional area of a can-annular type combustion chamber in aircraft design is an essential parameter that helps determine the size and geometry of the combustion chamber. The specific formula for calculating this area can vary depending on the design and geometry of the combustion chamber. However, a general approach to calculating the cross-sectional area (A) can be based on the mass flow rate (ṁ) and the velocity of the air-fuel mixture entering the chamber. The formula is as follows:
- A = Cross-sectional area of the combustion chamber inlet (in square meters, m²)
- ṁ = Mass flow rate of the air-fuel mixture (in kilograms per second, kg/s)
- ρ = Density of the mixture in the combustion chamber (in kilograms per cubic meter, kg/m³)
- V = Inlet velocity of the air-fuel mixture (in meters per second, m/s)