# Isentropic Mach number

(Difference between revisions)
 Revision as of 09:02, 16 August 2007 (view source)Jola (Talk | contribs)← Older edit Latest revision as of 09:06, 16 August 2007 (view source)Jola (Talk | contribs) m Line 5: Line 5: This gives the following formula for the isentropic Mach number: This gives the following formula for the isentropic Mach number: - :$M^{isentropic} = \sqrt{ \left( ( \frac{p_0^{freestream}}{p} ) ^{\frac{\gamma - 1}{\gamma}} - 1 \right) \frac{2}{\gamma - 1}}$ + :$M^{isentropic} = \sqrt{ \left( \left( \frac{p_0^{freestream}}{p} \right) ^{\frac{\gamma - 1}{\gamma}} - 1 \right) \cdot \frac{2}{\gamma - 1}}$ Where: Where:

## Latest revision as of 09:06, 16 August 2007

The isentropic Mach number is the Mach number you would have without any losses in the flow. This property is often used to investigate the ideal surface Mach number you would have without losses and walls without any friction (slip conditions). The isentropic Mach number is for example often plotted on turbomachinery blades. The isentropic Mach number can be computed from the isentropic flow relations using the following formula:

$\frac{p_0^{freestream}}{p}=(1+\frac{\gamma-1}{2}M^2)^{\frac{\gamma}{\gamma-1}}$

This gives the following formula for the isentropic Mach number:

$M^{isentropic} = \sqrt{ \left( \left( \frac{p_0^{freestream}}{p} \right) ^{\frac{\gamma - 1}{\gamma}} - 1 \right) \cdot \frac{2}{\gamma - 1}}$

Where:

$p_0^{freestream}$ is the Total pressure in the freestream outside of the boundary layers. Usually the inlet total pressure is used.
$p$ is the local Static pressure.
$\gamma$ is the ratio of specific heats, for air $\gamma = 1.4$.