współczynnik siły nośnej

Stall is a reduction in the lift coefficient generated by a wing as angle of attack increases.

However, these same characteristics make a wing have a very low lift coefficient, and poor performance at slow speeds.

This means that the Cz or aerodynamic lift coefficient is equal to 0.9.

The lift coefficient would then range between 0.08 and 0.4, with the aircraft experiencing up to 30% weight reduction as the fuel is consumed.

Note that in the graph here, there is still a small but positive lift coefficient with angles of attack less than zero.

Kites with good lift coefficients have a broader envelope, and are often more difficult to control into a landing.

Together, these things make a lift coefficient of 3.0.

This allows one to produce common curves such as lift coefficient versus angle of attack (shown).

While climbing, the flaps were extended, producing a high lift coefficient of 2.2.

If the angle of attack and velocity remain constant, an increase in the lift coefficient will result, which accounts for the "floating" effect.