What is the result of shock-induced separation of airflow near the wing root of a swept wing aircraft?

The phenomenon of shock-induced separation of airflow near the wing root of a swept wing aircraft primarily leads to a severe moment known as "Mach Tuck." As a swept wing aircraft approaches transonic speeds, the airflow can become supersonic at the leading edge of the wing, particularly in the root area. This is due to the wing's design which causes the flow to accelerate over the top surface.

When the wing reaches this critical point, the shock wave forms and can induce a sudden separation of the airflow. The result of this separation is a shift in the center of pressure toward the rear of the wing, which alters the aircraft's pitching moment. Specifically, it causes the nose of the aircraft to pitch down, creating a condition known as "Mach Tuck." This can lead to a significant loss of control if not managed properly, as the aircraft may experience an unexpected change in attitude and altitude.

In the context of the other choices, while increased drag and loss of lift do occur due to airflow separation, the defining characteristic is the resulting aerodynamic moment that leads to Mach Tuck. High-speed stall and sudden pitch-up, as well as severe porpoising, are related but are not directly the primary outcome of this specific shock-induced airflow separation phenomenon