Refer to figures.
The distribution of pressure is important in aerodynamics, since it determines:
- The amount of lift generated
- Any pitching moments
- The form drag of an aerofoil section

The lift and drag forces of a wing cross-section are dependent on the pressure distribution around the wing. The pressure distribution around an aerofoil is the resultant of the angle of the aerofoil chordline to the oncoming airflow, the angle of attack.

If a symmetrical aerofoil section is in a steady airstream at zero degrees Angle of Attack, a stagnation point forms on the leading edge.

The airflow velocity above and below the aerofoil increases by an equal amount and the static pressures reduce by an equal amount. Consequently, no pressure differential exists, and no net lift is created.