The velocity of air or gas within a Can Type Combustion Chamber in aircraft design can be calculated using the formula for mass flow rate (ṁ) and the cross-sectional area (A) of the Can Type Combustion Chamber.The formula is as follows:
- V = Velocity of the fluid (in meters per second, m/s)
- ṁ = Mass flow rate of the fluid (in kilograms per second, kg/s)
- ρ = Density of the fluid (in kilograms per cubic meter, kg/m³)
- A = Cross-sectional area of the Combustion inlet (in square meters, m²)