Lift Coefficient Calculator

Find the lift coefficient from lift force and flow conditions.

Lift force (N)

Air density (kg/m³)

Velocity

Wing area

Lift coefficient 0.2041

Formula: C_L = 2·L ÷ (ρ·v²·A)

Step-by-step with your numbers:

1. Values used:

2. Lift force = 5,000 N

3. Air density = 1.225 kg/m³

4. Velocity = 50

5. Wing area = 16

7. Lift coefficient = 0.2041

Did we solve your problem today?

The lift coefficient captures how effectively a wing generates lift.

The math behind it

From L = ½·ρ·v²·C_L·A, solve C_L = 2·L ÷ (ρ·v²·A).

5000 N lift, 50 m/s, 16 m² wing → C_L ≈ 0.255.

What sets C_L?

Airfoil shape and angle of attack, up to the stall point.