The formula for leading-edge slats is typically based on aerodynamic principles and specific aircraft design requirements. It involves factors such as airfoil shape, wing geometry, desired lift characteristics, and operational considerations.
Where:
- is the increase in maximum lift coefficient.
- is a coefficient representing the effectiveness of the slat system.
- is the area of the slats.
- is the total wing area.
- is the maximum deflection angle of the slats.