What may result from shock-induced separation of airflow near the wing root of a sweptback wing?

Shock-induced separation of airflow near the wing root of a sweptback wing can lead to a severe diving moment due to the disruption of airflow. When airflow separates from the wing surface, it often causes a significant change in the aerodynamic forces acting on the wing. Specifically, as the airflow separates, it leads to a loss of lift in that area, which in turn shifts the center of pressure. This shifting can cause the aircraft to pitch down abruptly, creating a diving moment.

In sweptback wings, high speeds can lead to shock waves forming on the upper surface, resulting in significant changes in pressure distribution across the wing. When these shock waves and resulting flow separations occur, they affect the control characteristics of the aircraft, often requiring immediate corrective action from the flight crew to maintain control.

While other choices may suggest positive effects like increased lift or improved stability, these outcomes are unlikely in the scenario of shock-induced separation, as the primary issue is the adverse effect on airflow and control surfaces, ultimately resulting in a more unstable condition for the aircraft.