In fluid dynamics, the flowfield near the origin corresponds to a stagnation point.

In 2-D, streamlines are concentric closed curves that cross only at stagnation points.

At a stagnation point, the velocity of the fluid is zero.

This information can be used to show that the pressure coefficient at a stagnation point is unity (positive one):

The streamline at a stagnation point is perpendicular to the surface of the body.

This same value appears at the downstream stagnation point, this high pressure is again need to decelerate the flow to zero speed.

The stagnation point on the topside of the airfoil then moves until it reaches the trailing edge.

As the airfoil continues on its way, there is a stagnation point at the trailing edge.

Once the initial transient effects have died out, the stagnation point is at the trailing edge as required by the Kutta condition.

The dividing line between the upper and lower streamtubes intersects the body at the stagnation points.