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. [1] With a given upstream Mach number, the post-shock Mach number can be calculated along with the pressure, density, temperature, and stagnation pressure ratios.

Pressure, Mach number and Wave Angle changes through oblique shock waves. ( γ = 7/5) Notation :

1.8050 1.8355 1.8661 1.8971 1.9282 1.0000 1.0167 1.0334 1.0502 1.0671

Normal Shock Waves For a normal shock 2 wave is perpendicular to flow (propagation) direction Shock is nonequilibrium process internally, but assume flow before shock flow after shock is in equilibrium is in equilibrium -1

May 13, 2021 · If the shock wave is perpendicular to the flow direction it is called a normal shock. On this slide we have listed the equations which describe the change in flow variables for flow across a normal shock.

1.0000E+00 1.0167E+00 1.0334E+00 1.0502E+00 1.0671E+00 1.0840E+00 1.1009E+00 1.1179E+00 1.1349E+00 1.1520E+00 1.1691E+00 1.1862E+00 1.2034E+00 1.2206E+00 1.2378E+00 1 ...

Pressure, Mach number and temperature changes through normal shock waves. Prandtl-Meyer angle and Mach angle for expanding flows. ( γ = 7/5)

The equations provide relations for continuous one-dimensional flow, normal and oblique shock waves, and Prandtl-Meyer expansions for both perfect and imperfect gases.

PM Fan and Oblique Shock Tables. Source: Aerodynamics for Engineers, Bertin & Smith. Oblique 2D Shock. Conical Shock.

Normal Shock Factors for an Ideal Gas with k=1.4 (e.g. Air) Ma1 Ma2 P2/P1 ρ2/ρ1 T2/T1 P02/P01 P1/P02