Discussion
Consider the following statements about a converging-diverging nozzle running with a supersonic exit:
1. The Mach number at the throat is exactly one.
2. The flow accelerates through the divergent section.
3. The static pressure rises through the divergent section.
Which of the statements given above is or are correct?
Answer: D
The first two describe correct operation on the supersonic branch. The third is wrong: as the supersonic flow accelerates in the diverging duct its static pressure falls. Pressure would rise there only on the subsonic branch, or across a shock standing in the divergent section.
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