Near Field Examination of Sonic/supersonic Nozzle flows

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dc.contributor.authorJraisheh, Ali
dc.date.accessioned2024-06-07T10:59:59Z
dc.date.available2024-06-07T10:59:59Z
dc.date.issued2023
dc.descriptionSupervisor: Kulkarni, Vinayak N
dc.description.abstractThis thesis presents a numerical study on compressible flow within and downstream sonic/supersonic nozzles. It is a close look on the effects of thermodynamics and geometry configuration on the gas flow inside and downstream the ducts. An in-house CFD solver is developed to accommodate the complex flow structure that accompanies the under expanded jet and impose the proper boundary conditions, in order to simulate the flow field. More focus is drawn to the phenomenon of Mach disk that occurs in case of highly under expanded flow, its location and height are thoroughly studied and analysed.
dc.identifier.otherROLL NO.186103002
dc.identifier.urihttps://gyan.iitg.ac.in/handle/123456789/2637
dc.language.isoen
dc.relation.ispartofseriesTH-3058
dc.titleNear Field Examination of Sonic/supersonic Nozzle flows
dc.typeThesis
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