Kostenloser Lift Coefficient Rechner
Berechnen Sie den lift coefficient CL aus lift force, air density, velocity, and wing area. Essential for aircraft und aerodynamic design.
Lift Coefficient (CL)
0.5553
Lift Coefficient (CL) vs Lift Force (L)
Formel
## 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.
Lösungsbeispiel
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
Häufig Gestellte Fragen
What is a typical lift coefficient for cruise flight?
During cruise, most transport aircraft operate at CL values between 0.3 and 0.6. Higher CL values are used during takeoff and landing when flaps and slats are deployed.
Can the lift coefficient exceed 1?
Yes. With high-lift devices such as flaps and slats, CL can reach 2.5 or higher. The coefficient is dimensionless and not bounded by 1.
How does altitude affect the lift coefficient needed?
At higher altitudes, air density drops, so for the same weight and speed the aircraft needs a higher CL. Alternatively, the aircraft flies faster to compensate for the lower density.
Lernen