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Calculate Mach Number of Flow at Exit Method to Calculate the Mach Number of the Flow at Exit 

Aerospace



How to Calculate the Mach Number of Flow at Nozzle Exit In order to calculate the Mach Number of the flow at nozzle exit we require the temperature at the nozzle exit which is denoted by Te in Kelvin (K). 

Furthermore, we also require the velocity of the flow in the nozzle exit denoted by Ve.
Since, speed of sound in the nozzle at exit is given by Speed of sound = ae = square root (gamma*R*Te)
where, Te is the temperature at nozzle exit, R is specific gas constant = 287 J/kg.K gamma for air = 1.4
So, the Mach Number of the flow at the Nozzle Exit is then,
Mach Number , Me = Ve/ae Mach Number is a nondimensional quantity and so it has no units.


Download Free Program to Calculate the Mach Number of the Flow at Exit

