Calculadora de Coeficiente de Sustentación — Fórmula

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.

Ejemplo Resuelto

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

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