# Lift Equation

## Lift

Lift depends on the density of the air, the square of the velocity, the air’s viscosity and compressibility, the surface area over which the air flows, the shape of the body, and the body’s **inclination** to the flow. In general, the dependence on body shape, inclination, air viscosity, and compressibility are very complex.

One way to deal with complex dependencies is to characterize the dependence by a single variable. For lift, this variable is called the lift coefficient, designated “C_{l}.” This allows us to collect all the effects, simple and complex, into a single equation. The lift equation states that lift **L** is equal to the lift coefficient **Cl** times the density **rho **(\(\bf\rho\)) times half of the velocity **V** squared times the wing area **A**.

\(\LARGE L=\mathit{Cl}\cdot\frac{\rho V^{2}}{2}\cdot A\)

## Determining Lift Coefficient

For given air conditions, shape, and inclination of the object, we have to determine a value for Cl to determine the lift. For some simple flow conditions, geometries, and low inclinations, engineers can determine the value of Cl mathematically. But, in general, this parameter is determined experimentally.

In many textbooks on aerodynamics, the density is given by the Greek symbol “rho” (Greek for “r”) as used in the figure. The combination of terms “density times the square of the velocity divided by two” is called the dynamic pressure and appears in Bernoulli’s pressure equation.