✈️ Lift Coefficient Calculator
Calculate the lift coefficient of a wing or airfoil from the lift force it generates, the air density, its airspeed, and its planform area.
What the lift coefficient is
The lift coefficient (CL) is a dimensionless number that describes how effectively a wing or airfoil shape converts airspeed into lift, independent of the aircraft’s size or speed. It depends on the airfoil’s shape, angle of attack, and flow conditions, and is a core value in aircraft and wing design.
The formula
The lift coefficient comes from rearranging the standard lift equation: CL = L / (0.5 × ρ × v² × A), where L is lift force, ρ is air density, v is airspeed, and A is the wing’s planform (reference) area. The term 0.5 × ρ × v² is known as dynamic pressure.
This calculator uses standard sea-level air density (1.225 kg/m³) as the default and is intended for general aerodynamics education and reference; real aircraft performance also depends on angle of attack, Reynolds number, and airfoil profile.