Mechanical & Civil Engineering
Aerodynamic Lift Calculator
Calculate the lift force produced by a wing given air density, velocity, area, and lift coefficient.
Your inputs
Change any value to update the result instantly.
Lift force
42,336 N
Dynamic pressure
2,205 Pa
Lift in kN
42.336 kN
Approx. weight supported
4,317.1 kg
What this calculator does
Aerodynamic Lift Calculator: Applies the standard aerodynamics or orbital-mechanics relationship so the force, efficiency or manoeuvre cost can be worked out from the flight inputs.
What your result means
The headline figure is the aerodynamic force, efficiency or manoeuvre cost implied by your flight inputs. Real vehicles carry additional losses and margins.
Formula and working
L = 0.5 × ρ × v² × S × CL
- 1
Collect the inputs
Air density = 1.225 kg/m³; Velocity = 60 m/s; Wing area = 16 m²; Lift coefficient = 1.2
- 2
Apply the formula
L = 0.5 × ρ × v² × S × CL
- 3
Result
Lift force = 42,336 N
Frequently asked questions
Symbols and assumptions
- rho
- Air density (kg/m³)
- v
- Velocity (m/s)
- S
- Wing area (m²)
- CL
- Lift coefficient
- • Standard-atmosphere and idealised flow or two-body orbital conditions are assumed.
- • Losses, gravity turn, atmospheric drag and vehicle-specific effects are not modelled unless the page names them.
Sources and review
Reviewed 2026-09-22 · Next review 2027-09-22
- • This is an educational estimate for learning and checking, not a design deliverable.
- • Real design must follow the governing code or standard for your jurisdiction and be reviewed and signed off by a qualified engineer.
- • Safety factors, load combinations and material certification are the responsibility of the designer, not of this page.
Important limitation
This is an educational estimate based only on the values and formula shown. Verify current rates, rules, units, and professional standards before relying on the result. It is not personalized financial or investment advice.
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