What is the movement of the center of pressure when the wingtips of a swept wing airplane are shock-stalled first?

When the wingtips of a swept wing airplane experience shock stall, the center of pressure moves inward and forward due to the redistribution of aerodynamic forces as the airflow separates from the wing. In this situation, the airflow around the wingtips becomes disrupted before it does at the wing root, causing a rapid loss of lift at the wingtips.

As the wingtips stall, the lift and drag produced by those areas decrease considerably, thus shifting the center of pressure more toward the centerline and slightly forward on the wing. This movement inward is influenced by the sweep of the wing, where a larger portion of the wing effectively continues to produce lift longer at the roots compared to the tips, leading to a change in the aerodynamic balance of the aircraft.

This behavior is crucial for understanding the stall characteristics and handling traits of swept wing configurations, which is a common design among modern jet aircraft. In contrast, other potential movements, such as outward or aft, do not accurately represent the aerodynamic changes occurring in the swept wing during a shock stall event.