Normal Shock Wave Equations - text only A graphical version of this slide is available. M is the Mach number, and a is the wedge angle.
Supersonic flow encounters a wedge and a shock is generated.
Flow upstream of the shock is denoted by a 0 and flow downstream of the shock is denoted by a 1. As an object moves through a gas, the gas molecules are deflected around the object. If the speed of the object is much less than the speed of sound of the gas, the density of the gas remains constant and the flow of gas can be described by conserving momentum and energy. As the speed of the object increases towards the speed of sound, we must consider compressibility effects on the gas. The density of the gas will vary locally as the gas is compressed by the object.