Foil Lift Coefficient Calculator

Lift force (L):

Density of fluid (ρ):

Flow velocity (V):

Reference area of the foil (A):

How This Is Calculated

$$ C_L = \frac{L}{0.5 \rho V^2 A} $$ where:

C_L = Lift coefficient (dimensionless)

L = Lift force (N)

ρ = Density of fluid (kg/m³)

V = Flow velocity (m/s)

A = Reference area of the foil (m²)

Assumptions

Flow is steady and two dimensional.
Fluid is incompressible.
Foil is thin.
Viscous effects are ignored.
Angle of attack is below stall angle.

Related Calculators

Angle of Attack

Aspect Ratio

Drag Coefficient

Lift Coefficient

Kutta-Joukowski Theorem