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formula for Mach number - Mechanical
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Assuming air to be an ideal gas, the formula to compute Mach number in a subsonic compressible flow is derived from Bernoulli's equation for M<1:[3]
{M}=\sqrt{\frac{2}{\gamma-1}\left[\left(\frac{q_c}{P}+1\right)^\frac{\gamma-1}{\gamma}-1\right]}
where:
\ M is Mach number
\ q_c is impact pressure and
\ P is static pressure
\ \gamma is the ratio of specific heat of a gas at a constant pressure to heat at a constant volume (1.4 for air).
The formula to compute Mach number in a supersonic compressible flow is derived from the Rayleigh Supersonic Pitot equation:
{M}=0.88128485\sqrt{\left[\left(\frac{q_c}{P}+1\right)\left(1-\frac{1}{[7M^2]}\right)^{2.5}\right]}
where:
\ q_c is now impact pressure measured behind a normal shock. |
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By gowtham, On - 2010-02-16 |
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