Physics

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Lift Coefficient Calculator.

Calculate aerodynamic lift coefficient from lift, density, speed, and area.

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Lift coefficient: 0.181406

Lift coefficient

0.000000

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Use Cases

Aerodynamic design of wings

Engineers use the lift coefficient to evaluate and compare the lift performance of different wing or airfoil designs at various speeds and conditions.

Example: Calculate CL for a wing with lift 5000 N, density 1.225 kg/m³, speed 50 m/s, area 20 m².

Educational physics experiments

Students and educators can use this calculator to verify theoretical lift coefficients in wind tunnel experiments or classroom demonstrations.

Example: Determine CL for a model airfoil with measured lift, known air density, and test speed.

Frequently Asked Questions

What is the lift coefficient?
The lift coefficient (CL) is a dimensionless number that relates the lift generated by a body (like an airfoil) to the fluid density, velocity, and reference area. It is used to characterize the lift efficiency of the body.
How is the lift coefficient calculated?
The lift coefficient is calculated using the formula: CL = 2 * Lift force / (Fluid density * Speed^2 * Reference area). This calculator uses that formula with the inputs you provide.
What units should I use?
Use consistent SI units: lift force in Newtons (N), fluid density in kilograms per cubic meter (kg/m³), speed in meters per second (m/s), and reference area in square meters (m²). The calculator will output the dimensionless lift coefficient.

Tips & Common Mistakes

Tips

  • Ensure all inputs are in SI units: Newtons, kg/m³, m/s, and m². Mixing units will give incorrect results.
  • Use the correct reference area: for a wing, this is typically the planform area (wing area as seen from above).
  • For accurate results, use the actual fluid density at your operating altitude or temperature, not standard sea-level value if conditions differ.
  • The lift coefficient is dimensionless; a higher value indicates a more efficient lift generation for given conditions.

Common Mistakes to Avoid

  • Using the wrong reference area, such as frontal area instead of planform area for a wing.
  • Forgetting to square the speed in the calculation, leading to an incorrect coefficient.
  • Inputting values in inconsistent units, like using pounds for force or feet per second for speed, without converting to SI.

Last updated: August 13, 2026