Free Lift Coefficient Calculator
Calculate the lift coefficient from measured lift force, air density, velocity, and wing area for aerodynamic analysis.
Lift Coefficient (CL)
0.5553
Lift Coefficient (CL) vs Lift Force (L)
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.
Example Calculation
An aircraft at sea level generates 50 kN of lift at 70 m/s with a 30 m² wing.
- 01Dynamic pressure q = 0.5 × 1.225 × 70² = 0.5 × 1.225 × 4900 = 3001.25 Pa
- 02CL = 50000 / (3001.25 × 30)
- 03CL = 50000 / 90037.5 = 0.5554
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