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Calculate Mach Number of Flow at Nozzle Throat Method to Calculate the Mach Number at Nozzle Throat 

Aerospace



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

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

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

