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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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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Abstract 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.
AbstractList Abstract 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.
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.
Author Ezhilmaran, G.
Khandai, Suresh Chandra
Pavithrabalan, S.
Udhayakumar, K.
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Cites_doi 10.1515/tjj.2011.012
10.2514/1.17637
10.1007/978-81-322-2743-4_75
10.1201/b15874
10.1017/S0022112075002352
10.2514/1.4447
10.1109/FPM.2015.7337340
10.1515/tjj-2016-0037
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References 2021080120240319215_j_tjj-2018-0034_ref_003_w2aab3b7d592b1b6b1ab2b3b3Aa
2021080120240319215_j_tjj-2018-0034_ref_010_w2aab3b7d592b1b6b1ab2b3c10Aa
2021080120240319215_j_tjj-2018-0034_ref_004_w2aab3b7d592b1b6b1ab2b3b4Aa
2021080120240319215_j_tjj-2018-0034_ref_005_w2aab3b7d592b1b6b1ab2b3b5Aa
2021080120240319215_j_tjj-2018-0034_ref_006_w2aab3b7d592b1b6b1ab2b3b6Aa
2021080120240319215_j_tjj-2018-0034_ref_007_w2aab3b7d592b1b6b1ab2b3b7Aa
2021080120240319215_j_tjj-2018-0034_ref_008_w2aab3b7d592b1b6b1ab2b3b8Aa
2021080120240319215_j_tjj-2018-0034_ref_009_w2aab3b7d592b1b6b1ab2b3b9Aa
2021080120240319215_j_tjj-2018-0034_ref_001_w2aab3b7d592b1b6b1ab2b3b1Aa
2021080120240319215_j_tjj-2018-0034_ref_002_w2aab3b7d592b1b6b1ab2b3b2Aa
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  doi: 10.1515/tjj.2011.012
– ident: 2021080120240319215_j_tjj-2018-0034_ref_010_w2aab3b7d592b1b6b1ab2b3c10Aa
  doi: 10.2514/1.17637
– ident: 2021080120240319215_j_tjj-2018-0034_ref_005_w2aab3b7d592b1b6b1ab2b3b5Aa
  doi: 10.1007/978-81-322-2743-4_75
– ident: 2021080120240319215_j_tjj-2018-0034_ref_009_w2aab3b7d592b1b6b1ab2b3b9Aa
  doi: 10.1201/b15874
– ident: 2021080120240319215_j_tjj-2018-0034_ref_001_w2aab3b7d592b1b6b1ab2b3b1Aa
  doi: 10.1017/S0022112075002352
– ident: 2021080120240319215_j_tjj-2018-0034_ref_002_w2aab3b7d592b1b6b1ab2b3b2Aa
  doi: 10.2514/1.4447
– ident: 2021080120240319215_j_tjj-2018-0034_ref_004_w2aab3b7d592b1b6b1ab2b3b4Aa
  doi: 10.1109/FPM.2015.7337340
– ident: 2021080120240319215_j_tjj-2018-0034_ref_003_w2aab3b7d592b1b6b1ab2b3b3Aa
– ident: 2021080120240319215_j_tjj-2018-0034_ref_007_w2aab3b7d592b1b6b1ab2b3b7Aa
  doi: 10.1515/tjj-2016-0037
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Snippet 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...
Abstract 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...
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SubjectTerms 47.40.Ki
47.40.Kz
circular exit
jet core
mixing characteristics
slanted perforated tabs
supersonic jet
Title Supersonic Jet Control by Tabs with Slanted Perforation
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Volume 38
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