 Quote by minger
I'm not an expert or even somewhat knowledgeable in these matters, but....I thought that if you had a convergent-divergent nozzle and flow reached sonic at the throat, then it would accelerate back up where it diverges (nozzles diverge for sonic,supersonic, diffusers converge, opposite of subsonic)
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This event could be possible too. The fact is when there are critical conditions just at the throat it can be a sudden transition to anyone of the regimes.
My actual question is if a convergent-divergent nozzle could decelerate a supersonic stream to a subsonic one without any shock wave, merely by the same principle of how it accelerates a subsonic stream to a supersonic one. Would it be mathematically and physically possible such a smooth transition?