Introduction

3.15.1 Introduction

Computes the mach number out of the corresponding pressure given or inverse. For the supersonic case it computes the Rayleigh-Pitot equation which takes the bow shock in from of the pitot tube into account.

The following properties are computed:

For $M <1$ the Pitot pressure ratio $p0/p$ will be computed for $M ≥1$ the Rayleigh-Pitot pressure ratio $p02/p1$ will be computed.

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I	Property	Description

1	$M$	Mach number.
2	$p$	Pressure ratio, see below