Supersonic Jet Control by Tabs with Slanted Perforation

Control of Mach 1.8 circular jet with slanted perforated tabs is studied experimentally. Two sets of perforated tabs were used for this study. The perforation angles were 0° and 30° with respect to axis of the nozzle. The blockage areas of the tabs were 5 %. The mixing enhancements caused by these t...

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Bibliographic Details
Published inInternational journal of turbo & jet-engines Vol. 38; no. 3; pp. 331 - 339
Main Authors Ezhilmaran, G., Khandai, Suresh Chandra, Pavithrabalan, S., Udhayakumar, K.
Format Journal Article
LanguageEnglish
Published De Gruyter 26.08.2021
Subjects
47.40.Ki
47.40.Kz
circular exit
jet core
mixing characteristics
slanted perforated tabs
supersonic jet
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Summary:Control of Mach 1.8 circular jet with slanted perforated tabs is studied experimentally. Two sets of perforated tabs were used for this study. The perforation angles were 0° and 30° with respect to axis of the nozzle. The blockage areas of the tabs were 5 %. The mixing enhancements caused by these tabs were studied in the presence of adverse and favorable pressure gradients, corresponding to nozzle pressure ratio (NPR) of 4, 5.74 and 8. For Mach number 1.8, jet NPR 4 corresponds to 30 % adverse pressure gradients and NPR 8 corresponds to 39.37 % favorable pressure gradients. The pressure decay characteristics and shadowgraph images of perforated tabs at different NPR were compared. There is 45 % and 65 % reduction in jet core length were observed for the 0° and 30° perforated tabs respectively in both pitot and shadowgraph experiments in comparison to uncontrolled jet.
ISSN:0334-0082
2191-0332
DOI:10.1515/tjj-2018-0034