where:
L = Lift force (N)
ρ = Air density (kg/m³)
V = Velocity relative to the air (m/s)
S = Wing area (m²)
CL = Lift Coefficient (Dimensionless)
- Aircraft is in steady-state flow conditions.
- Flow is incompressible.
- Flow across the entire wing surface is uniform.
- Wing behaves as a two-dimension airfoil.
- Ground effects are neglected.