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Lift Coefficient Calculator

Work out lift coefficient instantly with clear inputs, formula shown and shareable results.

About Lift Coefficient Calculator

Lift coefficient is the non-dimensional form of lift: CL = L / (q x S), where dynamic pressure q is half rho V squared. It tells you how hard the wing is working relative to its stalling capability, independent of speed and altitude.

Formula

Lift coefficient

CL = L / (0.5 x rho x V^2 x S)

Worked example

With the default values below, Lift Coefficient Calculator returns Lift coefficient of 0.3232. Change any input above and every figure here is recalculated in your browser.

Inputs used

Lift required
11,000 N
True airspeed
120 kt
Wing area
16.2 m²
Air density ratio
0.9 x

Results

Lift coefficient
0.3232
Dynamic pressure
2,100.81 Pa
Air density
1.1025 kg/m³
Margin to CLmax 1.6
1.2768

Step by step

  1. 1Values used
  2. 2Lift coefficient
  3. 3Lift coefficient= 0.3232
  4. 4Dynamic pressure= 2,100.81 Pa
  5. 5Air density= 1.1025 kg/m³
  6. 6Margin to CLmax 1.6= 1.2768

Assumptions and limits

  • The result is derived only from the 4 inputs listed above. Anything not among them is not part of the calculation.
  • In particular, this calculator does not take inflation, tax, fees or charges or compounding frequency into account.
  • Figures are rounded for display to 4 decimal places, so totals built from several rounded parts can differ slightly from the unrounded arithmetic.
  • Aviation results are planning estimates only. Always verify take-off, landing, fuel, weight and balance figures against the certified Aircraft Flight Manual, current performance charts and applicable aviation regulations before flight.

How these calculators are built and tested is described on the Methodology page. If a figure looks wrong, please report it.

Aviation results are planning estimates only. Always verify take-off, landing, fuel, weight and balance figures against the certified Aircraft Flight Manual, current performance charts and applicable aviation regulations before flight.

Frequently Asked Questions

What CL is typical in cruise?

Around 0.2-0.5 for a fast aircraft in cruise, rising to 1.2-1.6 clean at the stall and 2.0-2.8 with full flaps and slats deployed.

Why use a coefficient at all?

Because it removes speed and density, letting a single wind-tunnel curve describe the wing at every condition.

Related Calculators

Lift Coefficient Calculator – Calculate Lift coefficient