In case of the formation of shock in the divergent section of a C – D nozzle, the flow remains isentropic.(a) True(b) FalseI have been asked this question during an interview for a job.My question comes from Nozzles topic in chapter Quasi-One-Dimensional Flow of Aerodynamics

In case of the formation of shock in the divergent section of a C –

1.	In case of the formation of shock in the divergent section of a C – D nozzle, the flow remains isentropic.(a) True(b) FalseI have been asked this question during an interview for a job.My question comes from Nozzles topic in chapter Quasi-One-Dimensional Flow of Aerodynamics
Answer» Correct option is (b) False For explanation I would say: Usually the flow in the nozzle is CONSIDERED to be adiabatic because there is no heat TRANSFER. But when we try to achieve SUPERSONIC flow, there is formation of shock waves. Therefore the region between the THROAT the exit of the divergent nozzle does not have isentropic flow.

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In case of the formation of shock in the divergent section of a C – D nozzle, the flow remains isentropic.(a) True(b) FalseI have been asked this question during an interview for a job.My question comes from Nozzles topic in chapter Quasi-One-Dimensional Flow of Aerodynamics

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