Shock (fluid dynamics)

Shock is an abrupt discontinuity in the flow field and it occurs in flows when the local flow speed exceeds the local sound speed. ^[1] More specifically, it is a flow whose Mach number exceeds 1.

Explanation of phenomena

Shock is formed due to coalescence of various small pressure pulses. Sound waves are pressure waves and it is at the speed of the sound wave the disturbances are communicated in the medium. When an object is moving in a flow field the object sends out disturbances which propagate at the speed of sound and adjusts the remaining flow field accordingly.^{[ clarification needed ]} However, if the object itself happens to travel at speed greater than sound, then the disturbances created by the object would not have traveled and communicated to the rest of the flow field and this results in an abrupt change of property, which is termed as shock in gas dynamics terminology.

Shocks are characterized by discontinuous changes in flow properties such as velocity, pressure, temperature, etc. Typically, shock thickness is of a few mean free paths (of the order of 10⁻⁸ m). Shocks are irreversible occurrences in supersonic flows (i.e. the entropy increases).

Normal shock formulas

${\displaystyle \mathbf {T_{02}} =\mathbf {T_{01}} }$

${\displaystyle M_{2}=({\frac {{\frac {2}{\gamma -1}}+{M_{1}}^{2}}{{\frac {2\gamma }{\gamma -1}}{M_{1}}^{2}-1}})^{0.5}}$

${\displaystyle {\frac {p_{2}}{p_{1}}}={\frac {1+\gamma M_{1}^{2}}{1+\gamma M_{2}^{2}}}={\frac {2\gamma }{\gamma +1}}M_{1}^{2}-{\frac {\gamma -1}{\gamma +1}}}$

${\displaystyle {\frac {T_{2}}{T_{1}}}={\frac {1+{\frac {\gamma -1}{2}}M_{1}^{2}}{1+{\frac {\gamma -1}{2}}M_{2}^{2}}}={\frac {(1+{\frac {\gamma -1}{2}}M_{1}^{2})({\frac {2\gamma }{\gamma -1}}M_{1}^{2}-1)}{\frac {(\gamma +1)^{2}M_{1}^{2}}{2(\gamma -1)}}}}$

${\displaystyle {\frac {a_{2}}{a_{1}}}={({\frac {T_{2}}{T_{1}}})}^{0.5}}$

${\displaystyle {\frac {\rho _{2}}{\rho _{1}}}={\frac {p_{2}}{p_{1}}}{\frac {T_{1}}{T_{2}}}}$

${\displaystyle {\frac {p_{01}}{p_{1}}}=(1+{\frac {\gamma -1}{2}}M_{1}^{2})^{\frac {\gamma }{\gamma -1}}}$

${\displaystyle {\frac {p_{02}}{p_{2}}}=(1+{\frac {\gamma -1}{2}}M_{2}^{2})^{\frac {\gamma }{\gamma -1}}}$

Where, the index 1 refers to upstream properties, and the index 2 refers to down stream properties. The subscript 0 refers to total or stagnation properties. T is temperature, M is the mach number, P is pressure, ρ is density, and γ is the ratio of specific heats.

See also

• Mach number
• Sound barrier
• supersonic flow

References

1. Courant, Richard, and K.O. Friedrichs. Supersonic Flow and Shock Waves . Springer Science & Business Media, 1999. 2-3.