Lift Coefficient Calculator

Calculate the lift coefficient from measured lift force, air density, velocity, and wing area for aerodynamic analysis.

N
kg/m³
m/s
m²

Lift Coefficient (CL)

0.5553

Dynamic Pressure3,001.25 Pa

Lift Coefficient (CL) vs Lift Force (L)

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Formula

## Understanding the Lift Coefficient The lift coefficient (CL) is a dimensionless number that captures how effectively a wing generates lift relative to the dynamic pressure and its planform area. ### Formula **CL = L / (q * S) = L / (0.5 * rho * V² * S)** where L is the total lift force, rho is the freestream air density, V is the true airspeed, and S is the wing reference area. Typical CL values for cruise flight range from 0.3 to 0.6, while maximum CL at landing with flaps can reach 2.0 or more.

Esempio Risolto

An aircraft at sea level generates 50 kN of lift at 70 m/s with a 30 m² wing.

  1. 01Dynamic pressure q = 0.5 × 1.225 × 70² = 0.5 × 1.225 × 4900 = 3001.25 Pa
  2. 02CL = 50000 / (3001.25 × 30)
  3. 03CL = 50000 / 90037.5 = 0.5554