Rankine-Hugoniot equation

From Wikipedia, the free encyclopedia

This article may be too technical for most readers to understand, and needs attention from an expert on its subject. Please expand it to make it accessible to non-experts, without removing the technical details.

A schematic of a standing shock wave with the density

ρ

, velocity

u

, and temperature

T

in each region described by the Rankine-Hugoniot equations.

The Rankine-Hugoniot equation governs the behaviour of shock waves normal to the oncoming flow. It is named after physicists William John Macquorn Rankine and Pierre Henri Hugoniot, French engineer, 1851-1887.

The idea is to consider one-dimensional, steady flow of a fluid subject to the Euler equations and require that mass, momentum, and energy are conserved. This gives three equations from which the two speeds, $u 1$ and $u 2$ , are eliminated.

It is usual to denote upstream conditions with subscript 1 and downstream conditions with subscript 2. Here, $ρ$ is density, $u$ speed, $p$ pressure. The symbol $e$ means internal energy per unit mass; thus if ideal gases are considered, the equation of state is $p = ρ(γ - 1) e$ .

The following equations

$\rho_1u_1=\rho_2u_2\,$

$p_1+\rho_1u_1^2=p_2+\rho_2u_2^2$

$u_1\left(p_1+\rho_1e_1+\rho_1u_1^2/2\right)= u_2\left(p_2+\rho_2e_2+\rho_2u_2^2/2\right)$

are equivalent to the conservation of mass, momentum, and energy respectively. Note the three components to the energy flux: mechanical work, internal energy, and kinetic energy. Sometimes, these three conditions are referred to as the Rankine-Hugoniot conditions.

Eliminating the speeds gives the following relationship:

$2\left(h_2-h_1\right)=\left(p_2-p_1\right)\cdot \left(\frac{1}{\rho_1}+\frac{1}{\rho_2}\right)$

where $h=\frac{p}{\rho} + e$ . Now if the ideal gas equation of state is used we get

$\frac{p_1}{p_2}= \frac{(\gamma+1)-(\gamma-1)\frac{\rho_2}{\rho_1}} {(\gamma+1)\frac{\rho_2}{\rho_1}-(\gamma-1)}$

Thus, because the pressures are both positive, the density ratio is never greater than $(γ + 1) / (γ - 1)$ , or about 6 for air (in which $γ$ is about 1.4). As the strength of the shock increases, the downstream gas becomes hotter and hotter, but the density ratio $ρ 2 / ρ 1$ approaches a finite limit of 4 for a monatomic gas ( $γ$ = 5/3) and 6 for a diatomic gas ( $γ$ = 1.4).