Lift Coefficient Calculator

What Is the Lift Coefficient?

The lift coefficient $C_L$ is a dimensionless number that describes how efficiently a wing or airfoil generates lift at a given angle of attack and flow conditions. Aerodynamicists use it to compare wings independent of size and speed.

Lift Coefficient Formula

$$C_L = \frac{2L}{\rho v^2 A}$$

$L$ is lift force, $\rho$ is fluid density, $v$ is flow speed, and $A$ is reference wing area. Dynamic pressure $q = \frac{1}{2}\rho v^2$ lets you rewrite the formula as $C_L = L / (qA)$.

Typical Values

A cruising airliner wing might have $C_L \approx 0.4$ to $0.6$. High-lift devices during landing can exceed 2.0. Standard sea-level air density is about 1.225 kg/m³.

Frequently Asked Questions

What air density should I use?

At sea level under standard conditions, use 1.225 kg/m³. Density decreases with altitude and temperature.

Which wing area is used?

Reference area is usually planform (projected) wing area unless your problem specifies otherwise.

Is lift coefficient the same as angle of attack?

Related but not identical. $C_L$ depends on angle of attack, airfoil shape, Reynolds number, and Mach number.

Can I solve for lift force instead?

Yes. Select "Lift Force" and enter $C_L$, density, velocity, and wing area.

Does this work underwater?

Yes, with the appropriate fluid density. Replace air density with water density (about 1000 kg/m³).

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Lift Coefficient Calculator

What Is the Lift Coefficient?

Lift Coefficient Formula

Typical Values

Frequently Asked Questions

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