In aerodynamics, the normal shock tables are a series of tabulated data listing the various properties before and after the occurrence of a normal shock wave. With a given upstream Mach number, the post-shock Mach number can be calculated along with the pressure, density, temperature, and stagnation pressure ratios. Such tables are useful since the equations used to calculate the properties after a normal shock are cumbersome.

The tables below have been calculated using a heat capacity ratio to be 1.4 over the entire Mach number range leads to errors over 10% beyond Mach 5.

Normal shock table equations

, can be calculated using the equation below.

, and the upstream ambient pressure.

is shown next in the tables.

.

occurs after the normal shock. The ratio of stagnation temperatures remains constant across a normal shock since the process is adiabatic.

Note that before and after the shock the isentropic relations (comes from Bernoulli, assumes incompressible flow) because the flow is for Mach numbers greater than unity always compressible.

The normal shock tables (for γ = 1.4)

See also

• Normal shock

• Mach number

• Compressible flow

References

External links

• University of Cincinnati shock relations calculator

• Parkin Research Normal shock calculator