Lift Coefficient Calculator — Aerodynamics CL Formula
Use the fundamental aerodynamic lift equation L = ½ρv²ACL to solve for the lift coefficient CL or the lift force L. Enter air density, true airspeed and wing area, then leave either lift force or CL blank — the missing value is computed instantly.
N
kg/m³
m/s
m²
Dimensionless measure of lift generated per unit dynamic pressure and wing area
How does this calculator work?
L = ½ρv²ACL, rearranged: CL = 2L / (ρv²A). At sea level (ρ = 1.225 kg/m³), 60 m/s, 20 m² wing area and CL = 1.0 the lift force is 44,100 N (≈ 4,495 kgf). Typical cruise CL is 0.3–0.6; near-stall CL exceeds 2.5 for most wings.
Formula
How this is calculated
Lift is the aerodynamic force that keeps an aircraft airborne. The lift equation L = ½ρv²ACL links four variables: air density ρ (kg/m³), true airspeed v (m/s), wing reference area A (m²), and the dimensionless lift coefficient CL. The factor ½ρv² is called dynamic pressure (q) — the kinetic energy per unit volume of the airstream. Multiplying q by wing area gives the force per unit CL.
The lift coefficient CL encapsulates the aerodynamic efficiency of the wing at a given angle of attack and configuration. For a clean wing in cruise, CL is typically 0.3–0.6. With high-lift devices (flaps and slats) deployed for take-off or landing, CL rises to 1.5–3.0. Beyond the critical angle of attack, the airflow separates and CL drops sharply — this is a stall. Different aerofoils have different maximum CL values (CLmax), which this calculator cannot determine without full aerofoil data.
The air density default of 1.225 kg/m³ is the International Standard Atmosphere (ISA) value at sea level and 15 °C. Density decreases with altitude: at 10,000 m (FL330) it is roughly 0.413 kg/m³. Wing reference area is the planform area of the wing as defined by the manufacturer — always check which definition is used, as some sources exclude fuselage carry-through area.
Frequently asked questions
In cruise at altitude, CLs of 0.4–0.6 are common. At take-off with flaps extended, CL rises to 1.5–2.5. Maximum CL with full flap deployment (CLmax) for a typical airliner is around 2.5–3.5, depending on the high-lift system.
Lower air density at higher altitude reduces lift for the same speed and angle of attack. To maintain the same lift force, an aircraft must fly faster or increase its angle of attack (higher CL). Pilots use true airspeed (TAS) rather than indicated airspeed for the lift equation.
The wing reference area (also called wing area or planform area) is the projected area of the wing viewed from above, as defined by the manufacturer. It typically includes the fuselage carry-through section. A Boeing 737-800 has a wing area of about 124.6 m².
Also known as
TG we-Calculate Editorial Team. (2026). Lift Coefficient Calculator — Aerodynamics CL Formula [Online calculator]. TG we-Calculate. https://we-calculate.com/calculator/lift-coefficient-calculator
TG we-Calculate Editorial Team. "Lift Coefficient Calculator — Aerodynamics CL Formula." TG we-Calculate. 2026. https://we-calculate.com/calculator/lift-coefficient-calculator.
TG we-Calculate Editorial Team, "Lift Coefficient Calculator — Aerodynamics CL Formula," TG we-Calculate, 2026. [Online]. Available: https://we-calculate.com/calculator/lift-coefficient-calculator
@misc{wecalculate_lift_coefficient_calculator, title = {Lift Coefficient Calculator — Aerodynamics CL Formula}, author = {{TG we-Calculate Editorial Team}}, howpublished = {\url{https://we-calculate.com/calculator/lift-coefficient-calculator}}, year = {2026}, note = {TG we-Calculate} }
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