What would be the outcome of flying at an angle of attack that is higher than that for maximum lift/drag?

Flying at an angle of attack that is higher than that for maximum lift-to-drag ratio results in increased total drag. This happens because as the angle of attack exceeds the optimal point, the aircraft experiences a rise in induced drag alongside an increase in parasitic drag.

At the maximum lift-to-drag ratio, the aircraft achieves an ideal balance between lift and drag, allowing for the most efficient flight profile. When the angle of attack becomes too steep, the flow of air over the wings begins to separate, leading to a significant increase in drag, which negatively affects the aircraft's overall performance and efficiency.

Increased stability, increased control response, and decreased fuel consumption are not accurate outcomes of flying at an angle of attack beyond the optimal level. Typically, higher angles of attack could lead to loss of control or reduced stability, worsen response characteristics, and increase fuel consumption due to the higher drag, making option B the clear outcome in this scenario.