As the angle of attack of an airfoil increases, where will the center of pressure likely move?

As the angle of attack of an airfoil increases, the center of pressure typically moves toward the leading edge. This phenomenon occurs because, as the angle of attack rises, the airflow over the airfoil changes, leading to an increase in the pressure difference between the upper and lower surfaces. This shift in pressure results in the center of pressure moving forward.

When the angle of attack increases, the flow separation point moves further back on the airfoil due to the increased lift generated. Consequently, more lift is produced on the upper surface, and the force vector associated with lift tends to move forward, thus relocating the center of pressure closer to the leading edge. Understanding this behavior is crucial in designing airfoils and predicting their performance at various angles of attack, as it affects stability and control of the aircraft.