Sonic velocity at the throat of a convergent-divergent nozzle

[T C]

TL;DR Summary

Sufficiently pressurised compressible fluid is being released through a convergent-divergent nozzle. I want to know that whether irrespective of the geometry and inlet to throat ratio of the nozzle, do the velocity at the throat will always remain sonic?

Sufficiently pressurised (difference between inlet and release pressure is enough to create supersonic flow) gaseous fluid is being released through a convergent-divergent nozzle. And it's a known fact that if pressure difference is sufficient, a convergent-divergent nozzle can release gaseous fluid at supersonic velocity. I want to know that whether irrespective of the inlet to throat ratio and geometry of the divergent section, do the velocity at the throat will always remain sonic or it need some factors to keep the velocity sonic at the throat.

 

[boneh3ad]

Have you done any work to try to work out this problem on your own? If you are only looking for a yes/no answer, then you could get that from Google.

 

[T C]

How? Kindly guide me.

 

[boneh3ad]

Have you ever taken a compressible flow course or are you otherwise familiar with compressible flow?