Prandtl-Meyer function

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Varition in the Prandtl-Meyer function (

ν

) with Mach number (

M

) and ratio of specific heat capacity (

γ

). The dashed lines show the limiting value

ν m a x

as Mach number tends to infinity.

Prandtl-Meyer function describes the angle through which a flow can turn isentropically for the given initial and final Mach number. It is the maximum angle through which a sonic (M = 1) flow can be turned around a convex corner. For an ideal gas, it is expressed as follows,

$\begin{align} \nu(M) & = \int \frac{\sqrt{M^2-1}}{1+\frac{\gamma -1}{2}M^2}\frac{\,dM}{M} \\ & = \sqrt{\frac{\gamma + 1}{\gamma -1}} \cdot arctan \sqrt{\frac{\gamma -1}{\gamma +1} (M^2 -1)} - arctan \sqrt{M^2 -1} \\ \end{align}$

where, $\nu \,$ is the Prandtl-Meyer function, $M$ is the Mach number of the flow and $γ$ is the ratio of the specific heat capacities.

By convention, the constant of integration is selected such that $\nu(1) = 0. \,$

As Mach number varies from 1 to $\infty$ , $\nu \,$ takes values from 0 to $\nu_{max} \,$ , where

$\nu_{max} = \frac{\pi}{2} \bigg( \sqrt{\frac{\gamma+1}{\gamma-1}} -1 \bigg)$

For isentropic expansion,	$\nu(M_2) = \nu(M_1) + \theta \,$
For isentropic compression,	$\nu(M_2) = \nu(M_1) - \theta \,$

where, $θ$ is the absolute value of the angle through which the flow turns, $M$ is the flow Mach number and the suffixes "1" and "2" denote the initial and final conditions respectively.