Lift Coefficient Calculator
Calculate lift coefficient from measured lift, fluid density, speed, and reference area.
How to Use This Calculator
Measure or estimate inputs
Obtain lift force, fluid density, flow speed, and reference area.
Enter the values
Input all quantities in SI units for a dimensionless result.
Calculate Cl
Press Calculate to get the lift coefficient for analysis and comparisons.
Formula
Cl = 2L / (ρ V² A)
Where: Cl is lift coefficient, L is lift force, ρ is fluid density, V is free-stream speed, A is reference area.
Example: L = 500 N, ρ = 1.225 kg/m³, V = 30 m/s, A = 0.8 m² ⇒ Cl = 2·500 / (1.225·30²·0.8) ≈ 1.132.
About Lift Coefficient Calculator
The lift coefficient characterizes aerodynamic lift relative to dynamic pressure and reference area. It enables comparison across scales and conditions in wings, blades, and foils.
When to Use This Calculator
- Wind tunnel data reduction: Convert forces to dimensionless coefficients.
- Airfoil analysis: Compare performance across angles of attack.
- Design trade studies: Evaluate lift capability vs area and speed.
Why Use Our Calculator?
- ✅ Accurate: Uses standard aerodynamic relation.
- ✅ Clear: Inputs/outputs tailored for experiments and design.
- ✅ Helpful: Includes an example and guidance.
Frequently Asked Questions
What reference area should I use?
For wings, use planform area. For airfoils in 2D sections, use chord × span of the tested model or standardized area used in your data reduction.
Is Cl dimensionless?
Yes. Ensure all inputs are in consistent SI units to get a dimensionless result.
Does compressibility affect Cl?
The relation holds generally, but at high Mach numbers, compressibility and shocks can alter lift; empirical corrections may be necessary.