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]
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:
where:
\ q_c is now impact pressure measured behind a normal shock.
Courtesy:Wikipedia,Wiki Dictionary,NASA-USA
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