Lift⚠ unverified
Physics / Fluids · Compute the aerodynamic lift force
Parameters
| Input | Symbol | Unit | Default | Description |
|---|---|---|---|---|
| lift_coefficient | liftcoefficient | — | 1.0 | Lift coefficient, dimensionless |
| density | density | kg/m**3 | 1.0 | Fluid density |
| velocity | velocity | m/s | 1.0 | Free-stream flow speed |
| area | area | m**2 | 1.0 | Reference area |
| Output | Symbol | Unit | Description |
|---|---|---|---|
| result | L | N | Lift force, in newtons (N) |
The science & history
Understanding the Parameters
- $C_L$ — from airfoil/wing data; rises with angle of attack until stall. Not a universal constant.
- $\rho$, $v$ — enter via Dynamic Pressure $q = \tfrac12\rho v^{2}$.
- $A$ — typically planform area $b\cdot\bar{c}$ for wings.
- $L$ — for steady level flight, $L = W$ (weight); structure and performance size around $q C_L A$.
Derivation (Approaching a Proof)
Same dimensional construction as drag: force $\sim \rho v^{2} A$, with $C_L$ defined by
$$L = C_L\cdot\tfrac12\rho v^{2}\cdot A.$$
Circulation theory (Kutta–Joukowski) gives $L' = \rho v\Gamma$ per span for 2-D airfoils — a first- principles route to $C_L$ for idealised cases; real 3-D wings still use measured $C_L$.
History
The $C_L q A$ form and wind-tunnel coefficients became standard in early aviation and remain the language of flight mechanics.
Related Concepts: Drag, Dynamic Pressure, Reynolds Number, Mach Number, Thrust
Notes: Registry calculator lift (unverified). Empirical $C_L$; steady free-stream model.