Calculate the aerodynamic lift coefficient for an airfoil or wing.
Flight Parameters
N
kg/m³
m/s
m²
Aerodynamic Results
Enter flight parameters to calculate lift
About this calculator
Quick Reference
LLift Force (N)
C_LLift Coefficient
ρAir Density (kg/m³)
vVelocity (m/s)
AWing Area (m²)
Overview
The lift coefficient is a dimensionless number that describes how much lift an airfoil or wing produces at a given angle of attack. It's used by aerospace engineers to predict the lift-generating capabilities of different shapes.
💡
Pro Tips
Standard air density at sea level is approximately 1.225 kg/m³.
The formula is C_L = L / (0.5 * ρ * v² * A).
Most commercial aircraft wings have a maximum C_L around 1.5 to 2.5 (with flaps).
!
Fun Facts
"Wait, did you know that birds can change their wing shape in real-time to adjust their lift coefficient, something only the most advanced military jets can do?"
"The Wright brothers built their own wind tunnel to measure lift coefficients before they ever attempted their first flight at Kitty Hawk."
"A spinning baseball or golf ball also generates lift through the 'Magnus effect', which can be described with a special type of lift coefficient."
