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Lift Force Calculator

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

About Lift Force Calculator

Lift follows the same form as drag but with the lift coefficient: L = 0.5 rho v^2 Cl A. A 16 m2 wing at Cl 1.2 and 45 m/s generates about 23.8 kN, enough to hold 2430 kg aloft. Since lift goes with speed squared, halving speed quarters lift - which is why stall speed rises with weight and falls with air density.

Formulas

Lift force

L = 0.5 x rho x v^2 x Cl x A

Dynamic pressure

q = 0.5 rho v^2

Worked example

With the default values below, Lift Force Calculator returns Lift Force of 23,814.0. Change any input above and every figure here is recalculated in your browser.

Inputs used

Lift coefficient Clminimum 0
1.2
Wing areaminimum 0 m2
16 m2
Airspeedminimum 0 m/s
45 m/s
Air densityminimum 0 kg/m3
1.225 kg/m3

Results

Lift Force
23,814.0 N
Mass It Can Support
2,428.35 kg
Wing Loading
1,488.375 N/m2
Dynamic Pressure
1,240.313 Pa

Step by step

  1. 1Values used
  2. 2Lift force
  3. 3Dynamic pressure
  4. 4Lift Force= 23,814.0 N
  5. 5Mass It Can Support= 2,428.35 kg
  6. 6Wing Loading= 1,488.375 N/m2
  7. 7Dynamic Pressure= 1,240.313 Pa

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 3 decimal places, so totals built from several rounded parts can differ slightly from the unrounded arithmetic.

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

Frequently Asked Questions

Why does an aircraft need more speed at altitude?

Because air density falls, so the same lift requires a higher true airspeed. Indicated airspeed, which measures dynamic pressure, stays the same.

What limits the lift coefficient?

Stall. Beyond roughly 15 degrees of angle of attack the flow separates and Cl collapses; flaps and slats push the usable maximum higher.

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