Lift Calculator

Property to Calculate:

Lift force (L):

Air density (ρ):

Velocity relative to the air (V):

Wing area (S):

Lift Coefficient (C_L):

How This Is Calculated

$$ L = \frac{1}{2} \rho V^2 S C_L $$ where:

L = Lift force (N)

ρ = Air density (kg/m³)

V = Velocity relative to the air (m/s)

S = Wing area (m²)

C_L = Lift Coefficient (Dimensionless)

Assumptions

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.

Related Calculators

Drag

Lift-to-Drag Ratio

Rate of Climb

Stall Speed

Turn Radius