The amount of lift an aircraft wing produces is determined by the shape of the wing, the density of the air, the viscosity or compressibility of the air, the velocity of the air over the wing and the inclination of the wing in relation to the airflow. This is very complex. So the lift equation is: Lift = Coefficient x Density x Velocity2 x Wing Area divided by 2. For pilots we basically have control over three variables when it comes to lift. Firstly, on most aircraft we can control the flaps that change the camber (shape) and sometimes even the surface area of our wing. We can change the velocity of the airflow over the wing, and we can change the angle of attack of the wing in relation to the relative airflow. The Lift equation Ch.2 - How an aircraft generates lift
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