Experimental Investigation of Supersonic Jet Control Using Sonic Air Tabs

G Mahendra Perumal; S M Aravindh Kumar; S Elangovan; M Sundararaj

doi:10.17485/IJST/v16i39.1918

Article

Experimental Investigation of Supersonic Jet Control Using Sonic Air Tabs

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Indian Journal of Science and Technology

DOI: 10.17485/IJST/v16i39.1918

Year: 2023, Volume: 16, Issue: 39, Pages: 3343-3352

Original Article

Experimental Investigation of Supersonic Jet Control Using Sonic Air Tabs

G Mahendra Perumal^1,2, S M Aravindh Kumar^1*, S Elangovan², M Sundararaj²

¹Department of Aerospace Engineering, SRM Institute of Science and Technology, Kattankulathur, Chennai, 603203, India
²Department of Aeronautical Engineering, Bharath Institute of Higher Education and Research, Selaiyur, Chennai, 600126, India

*Corresponding Author
Email: [email protected]

Received Date:31 July 2023, Accepted Date:09 September 2023, Published Date:22 October 2023

This work is licensed under a Creative Commons Attribution 4.0 International License.

Abstract

Objectives: The primary objective of the study is to understand the influence of two sonic air tabs on the mixing characteristics of a supersonic (Mach 2.1) circular jet. Methods: In the high-speed open jet facility, a convergent-divergent nozzle delivering Mach 2.1 jet was controlled using two air tabs positioned at the nozzle exit. The injection pressure ratio of the air tabs varied from 3 to 6 for a nozzle pressure ratio of 3, 4, 5, and 6. Pitot pressure measurements and flow visualization were performed for controlled and uncontrolled jets. Findings: The results of the pitot pressure measurements showed a significant decrease in core length for the nozzle pressure ratios investigated. The core length reduction was attributed to the accelerated mixing of the Mach 2.1 jet with the surrounding fluid due to the air tabs. Furthermore, with the increase in the injection pressure ratio, the mixing enhancement due to the air tabs was observed to be increasing. The maximum reduction in core length occurred at an injection pressure ratio of 6 resulting in reductions of 86.1%, 64.9%, 61.1%, and 56.4% for nozzle pressure ratios 3, 4, 5, and 6, respectively. The visualization results confirmed the efficiency of the air tabs' in decreasing the strength of waves in the jet core region. Novelty: The novelty of this study lies in the use of two sonic air tabs for controlling supersonic jets. Unlike other control techniques, these air tabs can be activated or deactivated as needed without compromising the overall aircraft performance.

Keywords: Air Tab, Supersonic Jet, Injection Pressure Ratio, Nozzle Pressure Ratio, Shadowgraph

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Copyright

© 2023 Perumal et al. This is an open-access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited. Published By Indian Society for Education and Environment (iSee)