When does drag primarily increase in relation to the angle of attack?

Drag primarily increases in relation to the angle of attack both up to and beyond the stalling angle due to a combination of factors affecting flow separation and lift generation.

As the angle of attack increases from a low value, lift increases, but so does induced drag because the airflow near the wing stalls gradually, causing more turbulence. This turbulent flow creates additional drag as the wing approaches the stalling angle. At this point, the airflow remains attached to the wing, generating lift while increasing drag due to the heightened momentum of the disturbed flow.

Once the stalling angle is exceeded, the flow separates completely from the upper surface of the wing, leading to a dramatic increase in drag, known as form drag or pressure drag. This is when the wing is no longer able to generate sufficient lift because of the unfavorable airflow over its surface. The abrupt disruption in the smooth flow contributes to a significant rise in drag.

Thus, understanding the behavior of drag concerning the angle of attack is crucial, as it illustrates how aerodynamics impact aircraft performance at various angles. Recognizing that drag increases both as the angle of attack approaches and exceeds the stalling point allows for better management of aircraft performance during flight maneuvers and ensures safety.