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A normal shock wave is a discontinuity plane:
  • A
    across which the temperature drops suddenly.
  • B
    that is always normal to the surface.
  • C
    that is normal to the local flow.
  • D
    across which the pressure drops suddenly.

Refer to figure.
(Normal meaning perpendicular to the upstream flow).

Whenever supersonic airflow is slowed to subsonic speed without a change in direction, a ‘normal’ shock wave will form as a boundary between the supersonic and subsonic region. This means that some compressibility effects will occur before the aircraft reaches Mach 1.0.

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