Lift Coefficient Calculator — 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.
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.
Exemplo Resolvido
An aircraft at sea level generates 50 kN of lift at 70 m/s with a 30 m² wing.
- Dynamic pressure q = 0.5 × 1.225 × 70² = 0.5 × 1.225 × 4900 = 3001.25 Pa
- CL = 50000 / (3001.25 × 30)
- CL = 50000 / 90037.5 = 0.5554