Lift coefficient
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The lift coefficient (CL or CZ) is a number associated with a particular shape of an airfoil, and is incorporated in the lift equation to predict the lift force generated by a wing using this particular cross section.
The lift coefficient CL is equal to:
where L is the lift force, ρ is density, v is speed and A is area.
Note that the lift equation does not include terms for angle of attack — that is all wrapped up within the description of airfoil geometry, and the coefficient of lift incorporates this term. The graph for lift coefficient vs. angle of attack follows the same general shape for all airfoils, but the particular numbers will vary. The graph shows an almost linear increase in lift coefficient with increasing angle of attack, up to a maximum point, after which the lift coefficient falls away rapidly. This is known as the stall angle of the airfoil.
The coefficient of lift is a dimensionless number.
Note that in the graph here (which is generic, not representing any particular airfoil), there is still a small but positive lift coefficient with angles of attack less than zero. This is true of many actual designs; in particular those designs including asymmetry or camber: a curvature of the airfoil. As a consequence of the inertia of the air, the trailing edge of an airfoil will deflect air downwards more than the leading edge can deflect air upwards. The trailing edge of cambered airfoils has a downward tilt even when the airfoil as a whole is tilted to zero angle of attack. As a result, a cambered airfoil will deflect air downwards even at zero attack angle, and it will create a small amount of lift at zero and at small negative angles.
