In a converging-diverging nozzle with a choked throat and supersonic exit flow:
- The flow velocity stays unchanged throughout both the nozzle sections
- The gas accelerates through both the converging and diverging sections
- The gas decelerates through the diverging section as its pressure rises
ewanroles13 asked · 3 days ago
The wording of the question suggests the airflow is supersonic before reaching the convergent-divergent nozzle
PART66Online: Thank you for the report. You are right that the wording was ambiguous, and the stem has been corrected. The marked answer stands. What the question was describing is a nozzle at its design condition, with the throat choked and the exit flow supersonic. The gas arrives subsonic, accelerates through the converging section to reach Mach 1 at the throat, and then keeps accelerating through the diverging section as the now supersonic flow expands. Your reading was the reasonable one to take, and it is exactly why the stem needed changing. The area effect reverses either side of Mach 1: a converging duct accelerates subsonic flow, but it decelerates flow that is already supersonic. So on your reading of the old stem none of the three options would have been correct, which makes the wording a real defect rather than a matter of taste. Elsewhere in the bank that distinction is made explicit, with separate items keying air that enters a converging duct at sonic speed as decelerating. The stem now reads: In a converging-diverging nozzle with a choked throat and supersonic exit flow: The explanation shown after answering has been tightened in the same way, and it now states that the area effect depends on the local Mach number. Please keep the reports coming.