Lift Equation Calculator
A 16.2 m² wing at 60 m/s and C_L = 0.5 in sea-level air produces 17860.5 N of lift, enough to support about 1820 kg.
Sea level ISA 1.225 kg/m³; use the standard atmosphere calculator for altitude.
17860.5 N
- In kN
- 17.8605 kN
- In mN
- 17860500 mN
- In lbf
- 4015.200128 lbf
- In kgf
- 1821.264142 kgf
- In dyn
- 1786050000 dyn
- Dynamic pressure q = ½ρV²
- 2205 Pa
- Mass supported L/g
- 1821.264142 kg
- Drag
- the same equation with C_D in place of C_L
Step-by-step solution
- L = ½ × ρ × V² × S × C_L
- L = ½ × 1.225 × 60² × 16.2 × 0.5
- L = 17860.5 N
Lift Equation Formula
L = ½ ρ V² S C_L
ρ air density, V true airspeed, S wing area, C_L lift coefficient; drag uses C_D the same way
Worked Example
A 16.2 m² wing at 60 m/s and C_L = 0.5 at sea level:
- L = ½ × ρ × V² × S × C_L
- L = ½ × 1.225 × 60² × 16.2 × 0.5
- L = 17860.5 N
In mN: 17860500 mN · In lbf: 4015.200128 lbf · In kgf: 1821.264142 kgf · In dyn: 1786050000 dyn · Dynamic pressure q = ½ρV²: 2205 Pa · Mass supported L/g: 1821.264142 kg · Drag: the same equation with C_D in place of C_L
GATE tip
In level flight L = W, so C_L = 2W/(ρV²S). Higher altitude (lower ρ) at the same EAS needs the same C_L; at the same TAS it needs more.
More Airplane Performance Calculators
-
Drag Polar Calculator
C_D = C_D0 + K C_L², K = 1/(πeAR)
(L/D)max = 1/(2√(C_D0 K)) at C_L = √(C_D0/K)
Example: C_D0 = 0.025, AR = 8, e = 0.8 at C_L = 0.5: Drag coefficient C_D = 0.037434.
-
Stall Speed Calculator
V_s = √(2W / (ρ S C_L,max))
in a turn V_s√n; manoeuvring speed V_A = V_s√n_max
Example: An 1100 kg aircraft with a 16.2 m² wing and C_L,max = 1.6 at sea level: Stall speed V_s = 26.0667 m/s.
-
Take-off Distance Calculator
s_LO ≈ 1.44 W² / (g ρ S C_L,max T)
lift-off at 1.2 V_s; drag and rolling friction neglected (Anderson)
Example: An 1100 kg aircraft, 16.2 m², C_L,max 1.6, 3 kN thrust at sea level: Ground roll s_LO ≈ 179.381 m.
-
Turn Performance Calculator
R = V² / (g tan φ), ω = g tan φ / V
n = 1/cos φ; standard-rate turn 3°/s
Example: A 100-knot turn at 30° of bank: Turn radius R = 467.43 m.
Frequently asked questions
Why V squared?
Lift is proportional to dynamic pressure ½ρV²: doubling the speed quadruples the lift at the same angle of attack, so the aircraft must fly at a lower C_L.
How do I find the C_L needed for level flight?
Set L = W and choose “lift coefficient”: C_L = 2W/(ρV²S).
Sources
- The International System of Units (SI), 9th edition (SI Brochure), Bureau International des Poids et Mesures .
Last reviewed: . Factors are stored exactly and computed with 50-digit decimal arithmetic. See how we verify conversion factors.
Cite this page
APA
Scientific Converters. (2026, October 15). Lift Equation Calculator. Retrieved October 25, 2026, from https://scientificconverters.com/calculators/lift-equation-calculator/
IEEE
Scientific Converters, "Lift Equation Calculator," scientificconverters.com. Accessed: Oct. 25, 2026. [Online]. Available: https://scientificconverters.com/calculators/lift-equation-calculator/