The cross-sectional area of a turbine blade in aircraft design is a critical parameter that helps determine the size and geometry of the turbine blade. The specific formula for calculating this area can vary depending on the design and geometry of the turbine blade. 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 fluid entering the turbine. The formula is as follows:
- A = Cross-sectional area of the turbine inlet (in square meters, m²)
- 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)
- V = Inlet velocity of the fluid (in meters per second, m/s)