How does induced drag change as the angle of attack increases in a stall condition?

In stall conditions, as the angle of attack increases, the lift produced by the wings reaches a maximum and then begins to decrease sharply. Induced drag, which is a byproduct of lift generation, is directly related to the amount of lift being produced. At lower angles of attack, induced drag is relatively low because lift is being generated efficiently. However, as the angle of attack increases and the aircraft approaches stall, the lift diminishes and the induced drag experiences a notable increase.

When the aircraft reaches a stall, the airflow separation occurs over the wing, resulting in a sudden drop in lift. Nevertheless, during this transition, induced drag does not follow a simple decreasing trend; instead, it typically increases due to the increasing adverse pressure gradients and the presence of vortex formations at higher angles of attack. Thus, despite the overall reduction in lift, the interaction between airflow and wing shape leads to a rise in induced drag.

This understanding clarifies why the correct assertion aligns with the principle that induced drag is influenced by variations in lift, particularly under high angles of attack where stall conditions are present.