About

Lift is the mechanical aerodynamic force generated by a solid object moving through a fluid. For aircraft design, accurately predicting lift is essential to ensure the vehicle can overcome gravity. This calculator utilizes the fundamental Lift Equation. It is critical to adjust for Air Density (ρ), which decreases with altitude; a wing that generates sufficient lift at sea level may stall at higher elevations if velocity or angle of attack is not increased. This tool simplifies the variable selection for students and hobbyists.

Formulas

The Lift Force (L) is calculated using the dynamic pressure and the lift coefficient:

L = C_L × 12 ρ v² A

Where C_L is the dimensionless Lift Coefficient, ρ is Air Density, v is Velocity, and A is the Wing Area.

Reference Data

Altitude (m)	Air Density ρ (kg/m³)	Temp (°C)
0 (Sea Level)	1.225	15.0
1000	1.112	8.5
2000	1.007	2.0
3000	0.909	-4.5
5000	0.736	-17.5
10000	0.414	-50.0
15000	0.195	-56.5
20000	0.088	-56.5

Frequently Asked Questions

Cl is determined by the shape of the airfoil and the Angle of Attack (AoA). A flat plate has a lower Cl than a cambered airfoil. Increasing AoA increases Cl up to the "Stall Point," after which lift drops dramatically.

Lift depends on air molecules hitting the wing. At high altitudes, air density ($ ho$) is lower, meaning fewer molecules are available to generate pressure. To maintain lift, the aircraft must fly faster ($v^2$) or increase the wing area ($A$).

The standard physics formula requires area in square meters ($m^2$). If you use square feet, you must convert it, or the result in Newtons will be incorrect.

Yes. Since velocity is squared ($v^2$), doubling your speed quadruples the lift. This is why takeoff and landing (low speeds) require flaps to artificially increase wing area and camber.