Manipulation of Supersonic Jet using Grooved Tabs
This study experimentally evaluated the mixing augmentation of twin tabs mounted along a diameter at the outlet of a convergent-divergent Mach 1.62 circular nozzle. The usefulness of the plain and grooved tabs is examined at various expansion levels prevailing at nozzle outlet. The tab's perfor...
| Main Authors: | , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
Isfahan University of Technology
2024-02-01
|
| Series: | Journal of Applied Fluid Mechanics |
| Subjects: | |
| Online Access: | https://www.jafmonline.net/article_2404_30ee2f8d71b708906d826879b71f4ca9.pdf |
| _version_ | 1797294866401591296 |
|---|---|
| author | A. K. Mali T. Jana M. Kaushik S. Thanigaiarasu |
| author_facet | A. K. Mali T. Jana M. Kaushik S. Thanigaiarasu |
| author_sort | A. K. Mali |
| collection | DOAJ |
| description | This study experimentally evaluated the mixing augmentation of twin tabs mounted along a diameter at the outlet of a convergent-divergent Mach 1.62 circular nozzle. The usefulness of the plain and grooved tabs is examined at various expansion levels prevailing at nozzle outlet. The tab's performance is assessed through pitot pressure distribution measured along and perpendicular to the jet centerline at different nozzle pressure ratios (NPRs). The shadowgraph technique visualized the shocks and expansion fans in uncontrolled and controlled jets. With the introduction of uncorrugated or plain tabs at the nozzle outlet operating under overexpanded conditions corresponding to NPR 4, the supersonic length (SL) was decreased only by 35.4%. On the other hand, the corrugated or grooved tabs under similar conditions decreased the SL substantially. Interestingly, the performance of grooved tabs was best at underexpanded conditions associated with NPR 6, where the SL was reduced by about 88%. The pressure profiles also established the superiority of tabs with grooved edges in mixing augmentation without introducing any significant asymmetry to the flow field. In addition, the Shadowgraph images also confirmed the weakening of shock strength and reduction of shock-cell length in the case of grooved tabs at the nozzle exit compared to the plain nozzle. |
| first_indexed | 2024-03-07T21:38:18Z |
| format | Article |
| id | doaj.art-2fb1fe7402b24d209aee936161119acb |
| institution | Directory Open Access Journal |
| issn | 1735-3572 1735-3645 |
| language | English |
| last_indexed | 2024-03-07T21:38:18Z |
| publishDate | 2024-02-01 |
| publisher | Isfahan University of Technology |
| record_format | Article |
| series | Journal of Applied Fluid Mechanics |
| spelling | doaj.art-2fb1fe7402b24d209aee936161119acb2024-02-26T10:37:22ZengIsfahan University of TechnologyJournal of Applied Fluid Mechanics1735-35721735-36452024-02-011751027103810.47176/jafm.17.05.23262404Manipulation of Supersonic Jet using Grooved TabsA. K. Mali0T. Jana1M. Kaushik2S. Thanigaiarasu3Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur – 721302, IndiaDepartment of Aerospace Engineering, B.M.S. College of Engineering, Bengaluru - 560019, IndiaDepartment of Aerospace Engineering, Indian Institute of Technology, Kharagpur – 721302, IndiaDepartment of Aerospace Engineering, MIT Campus, Anna University, Chennai – 600044, IndiaThis study experimentally evaluated the mixing augmentation of twin tabs mounted along a diameter at the outlet of a convergent-divergent Mach 1.62 circular nozzle. The usefulness of the plain and grooved tabs is examined at various expansion levels prevailing at nozzle outlet. The tab's performance is assessed through pitot pressure distribution measured along and perpendicular to the jet centerline at different nozzle pressure ratios (NPRs). The shadowgraph technique visualized the shocks and expansion fans in uncontrolled and controlled jets. With the introduction of uncorrugated or plain tabs at the nozzle outlet operating under overexpanded conditions corresponding to NPR 4, the supersonic length (SL) was decreased only by 35.4%. On the other hand, the corrugated or grooved tabs under similar conditions decreased the SL substantially. Interestingly, the performance of grooved tabs was best at underexpanded conditions associated with NPR 6, where the SL was reduced by about 88%. The pressure profiles also established the superiority of tabs with grooved edges in mixing augmentation without introducing any significant asymmetry to the flow field. In addition, the Shadowgraph images also confirmed the weakening of shock strength and reduction of shock-cell length in the case of grooved tabs at the nozzle exit compared to the plain nozzle.https://www.jafmonline.net/article_2404_30ee2f8d71b708906d826879b71f4ca9.pdfshock-cellsupersonic lengthtabjet mixingflow visualization |
| spellingShingle | A. K. Mali T. Jana M. Kaushik S. Thanigaiarasu Manipulation of Supersonic Jet using Grooved Tabs Journal of Applied Fluid Mechanics shock-cell supersonic length tab jet mixing flow visualization |
| title | Manipulation of Supersonic Jet using Grooved Tabs |
| title_full | Manipulation of Supersonic Jet using Grooved Tabs |
| title_fullStr | Manipulation of Supersonic Jet using Grooved Tabs |
| title_full_unstemmed | Manipulation of Supersonic Jet using Grooved Tabs |
| title_short | Manipulation of Supersonic Jet using Grooved Tabs |
| title_sort | manipulation of supersonic jet using grooved tabs |
| topic | shock-cell supersonic length tab jet mixing flow visualization |
| url | https://www.jafmonline.net/article_2404_30ee2f8d71b708906d826879b71f4ca9.pdf |
| work_keys_str_mv | AT akmali manipulationofsupersonicjetusinggroovedtabs AT tjana manipulationofsupersonicjetusinggroovedtabs AT mkaushik manipulationofsupersonicjetusinggroovedtabs AT sthanigaiarasu manipulationofsupersonicjetusinggroovedtabs |