Home
Back
Coefficient of Lift Formula:
| From: | To: |
The Coefficient of Lift (CL) is a dimensionless number that describes the lift generated by an airfoil or lifting body relative to the dynamic pressure of the fluid flow and the reference area. It quantifies the effectiveness of a wing or airfoil in generating lift.
The calculator uses the lift coefficient formula:
Where:
Explanation: The coefficient relates the lift force to the dynamic pressure and wing area, allowing comparison of lift performance across different aircraft and conditions.
Details: The lift coefficient is fundamental in aerodynamics for aircraft design, performance analysis, and flight testing. It helps engineers optimize wing shapes and predict aircraft behavior under various flight conditions.
Tips: Enter lift force in Newtons, dynamic pressure in Pascals, and reference area in square meters. All values must be positive numbers greater than zero.
Q1: What is a typical range for lift coefficient?
A: For most aircraft, CL ranges from 0.1 to 2.0, with maximum values around 1.5-2.0 for conventional airfoils at high angles of attack.
Q2: How does angle of attack affect lift coefficient?
A: Lift coefficient generally increases with angle of attack up to the stall angle, after which it decreases sharply due to flow separation.
Q3: What is dynamic pressure (q)?
A: Dynamic pressure is given by \( q = \frac{1}{2} \rho V^2 \), where ρ is air density and V is airspeed. It represents the kinetic energy per unit volume of air.
Q4: Why is lift coefficient dimensionless?
A: It's dimensionless because it represents a ratio of forces (lift force to dynamic force), allowing comparison across different scales and conditions.
Q5: How is reference area defined?
A: For aircraft, reference area is typically the wing planform area. For other applications, it may be the frontal area or another characteristic area.