Introduction

Compressible Flow Subroutine Library
Programming Reference Manual
Version 1.0 DD-00008-110

3.10.1 Introduction

These functions compute the thermodynamic properties across a normal shock wave, assuming a calorically perfect gas and an adiabatic and frictionless flow, as described in [naca1135]. It can compute the following set of properties given one of the properties in conjunction with a specific heat ratio $γ$ of the gas medium.

The following equations govern normal shock waves as implemented in the function group:
Equation of Mass

p1u1 =p2u2

Equation of Momentum

p1+ ρ1u21=p2 +ρ2u22

Equation of Energy

1u21+h1 = 1 u22+h2 [adiab] 2 2

Normal Shock Waves are classified by the following properties, where the subscript $1,2$ refers to upstream and downstream, respectively.

The following properties are computed:

Table 8: Normal shock properties


I	Property	Description

1	$M1n$	Upstream mach number
2	$M2n$	Downstream mach number
3	$p2/p1$	Pressure ratio
4	$ρ /ρ 2 1$	Density ratio
5	$T2/T1$	Temperature ratio
6	$p02/p01$	Stagnation pressure ratio

[next] [prev] [prev-tail] [front] [up]