The shock waves induce changes in the boundary layer and pressure distribution over the body surface.

An airfoil at a given angle of attack will have what is called a pressure distribution.

This pressure distribution is simply the pressure at all points around an airfoil.

The effect that pressure distribution has on a surface is known as the form effect.

The resulting pressure distribution is asymmetrical and is shifted to the right.

The Mouse began the tedious check of pressure distribution and phase readings.

This solution gave the exact pressure distribution around an airfoil of arbitrary shape.

Vortices are then formed changing the pressure distribution along the surface.

At the same time the slightly unstable design of the sole improves pressure distribution in the feet.

The flap changed the center of pressure distribution so that the wing would not lose its lift.