The
Lift equation is a formula, for the amount of lift, a wing produces.
It
is: L=CL
x
1/2
x
ρ x V2
x
A
“CL“
is the lift coefficient, a number, depending on the shape of the
wing. It has a big influence on the created amount of lift, but is
mostly set by the manufacturer. The only ways for the pilot to adjust
this number is by in- or decreasing the angle of attack or to change
the position of the flaps.
“ρ”
is the density of the air. This the pilot only can adjust by climbing
or decanting. But it has just a little impact, because with less
density there is less drag and you can fly faster.
“V”
is the speed of the aircraft. It is the easiest way for the pilot to
change the amount of Lift created by the wing. Also, because it gets
squared, it has the biggest impact on the outcome.
“A”
is the wing area. Also here the only way for the pilot to adjust this
component is to change the position of the flaps.
