Details

This Demonstration uses the formula , where is the force of lift, is air density, is velocity, is reference area, and is the coefficient of lift, to find the altitude of equilibrium by setting the force of lift equal to the weight, then solving for the air density, and calculating the corresponding altitude. The coefficient of lift depends on the angle of attack and the shape of the airfoil, which is constant in this Demonstration. The coefficient of lift increases with the angle of attack up to the critical angle of attack (about 17 degrees here), after which the aircraft is considered to be stalled. Post-stall sustained flight is possible although very uncommon, because a stall usually occurs due to a slow airspeed or high forces, not because the wing is mounted to the aircraft at a high angle.

Similarly, the formula is used to find the force of drag, where is the coefficient of drag. Because there are several types of drag, including form drag and induced drag, the coefficient of drag typically decreases gradually until the angle of attack is around 6 degrees, then begins to increase sharply as the angle of attack is increased further.

Although it does not provide the maximum amount of lift or the least amount of drag, the ideal angle of attack is usually considered to be when the lift to drag ratio is at its highest. The maximum is usually achieved when the angle of attack is just above the point of minimum drag, and is around 7 degrees in this case.

Snapshot 1: an angle of attack with a high

Snapshot 2: an angle of attack past the critical angle

Snapshot 3: a negative angle of attack