Experimental study of jet-tab method with different tab lengths
-
Manikandan Subramaniyan
,
Vijayaraja Kengaiah
Abstract
This study examines the effectiveness of using a tab to create a significant force for altering thrust vectoring. Experiments were conducted in a high-speed jet facility to analyze the pressure distribution on tabs with different X/D ratios of 0.3, 0.5, and 0.7, which directly impact thrust vectoring. The tabs were attached at the nozzle exit. Based on the observed pressure values for these configurations, force calculations were made for nozzles operating at exit Mach numbers of 1.6, 1.8, and 2.0. All tests were performed at a fixed sector angle of 120°. The Experiment results indicate a substantial improvement in effectiveness with longer tabs and higher Mach numbers. Specifically, the force increases as the exit Mach numbers rise. An 8 % increase in force is observed when the Mach number rises from 1.6 to 1.8, followed by a subsequent 3.36 % increase when the Mach number goes from 1.8 to 2. Furthermore, a linear relationship was found between the force on the tab and the X/D ratio. There is a 93 % increase in force when the X/D ratio changes from 0.3 to 0.5 and a 14.5 % increase when it changes from 0.5 to 0.7. The maximum force occurs at Mach 2 with an X/D ratio of 0.7. The utilization of simple tabs for thrust vector control (TVC) is a subject of considerable relevance to the aerospace sector. This technique provides a mechanically simplified and mass-efficient TVC solution, which stands to confer several key benefits. These include increased agility for tactical aircraft, economical attitude control for missiles and rockets, and enhanced handling during critical flight phases such as short take-offs and landings. Consequently, the further development of tab-based TVC could yield substantial improvements in the reliability and performance of next-generation aircraft and spacecraft.
Acknowledgments
Authors would like to acknowledge the AR&DB funds for carrying out this work.
-
Research ethics: Not applicable.
-
Informed consent: Informed consent was obtained from all individuals included in this study.
-
Author contributions: All authors have accepted responsibility for the entire content of this manuscript and approved its submission.
-
Use of Large Language Models, AI and Machine Learning Tools: None declared.
-
Conflict of interest: The authors state no conflict of interes.
-
Research funding: AR&DB (Aeronautical Research and Development Board) Project No – 1946.
-
Data availability: Not applicable.
References
1. Jyothy, VM, Wessley, GJJ. Study of jet tabs in 2D convergent–divergent nozzle for thrust vectoring in aerial vehicles. Int J Intell Unmanned Syst 2022;12:117–32.10.1108/IJIUS-11-2022-0131Search in Google Scholar
2. Li, Y, Zhou, Y, Huang, J, Wang, Z, Zhu, S, Wu, K, et al.. Design of a flying humanoid robot based on thrust vector control. arXiv preprint arXiv:2108.11557. 2021.Search in Google Scholar
3. Ahmed, AR, Subramaniyan, M, Venkataraman, S, Thamizhselvan, SV. Numerical investigation of force over the horizontal jet tab of various sector angles fixed to the convergent-divergent nozzle exit. Trans Jpn Soc Aeronaut Space Sci 2024;41:699–705.10.1515/tjj-2023-0107Search in Google Scholar
4. Thanigaiarasu, S, Elangovan, S, Rathakrishnan, E. Experimental study on the effect of tabs with asymmetric projections on the mixing characteristics of subsonic jets. J Appl Fluid Mech 2013;6:275–82.Search in Google Scholar
5. Rathakrishnan, E. Characteristics of sonic jets with tabs. AIAA J Propul Power 2009;25:764–71.Search in Google Scholar
6. Zaman, KBMQ, Reeder, MF, Samimy, M. Control of an axisymmetric jet using vortex generators. AIAA J 1994;32:583–90.10.1063/1.868316Search in Google Scholar
7. Jayaprakash, S, Thanigaiarasu, S, Elangovan, S, Rathakrishnan, E. Effect of tab geometry and its orientation on under-expanded sonic jets. J Aero Eng 2014;28:1020–33.Search in Google Scholar
8. Zaman, KBMQ, Reeder, MF, Samimy, M. Supersonic jet mixing enhancement by ‘delta-tabs’. AIAA J 1995;33:2242–7.10.2514/3.12598Search in Google Scholar
9. Khan, SA, Rathakrishnan, E. Control of suddenly expanded flow with micro jets. AIAA J 2003;41:1140–4.10.1515/TJJ.2003.20.1.63Search in Google Scholar
10. Jayaprakash, S, Thanigaiarasu, S, Elangovan, S, Rathakrishnan, E. Influence of tab geometry and its orientation on under-expanded sonic jets. Exp Therm Fluid Sci 2015;65:22–30.Search in Google Scholar
11. Thanigaiarasu, S, Elangovan, S, Rathakrishnan, E. Investigation of jet mixing characteristics using slotted rectangular tabs. J Aero Technol Manag 2016;8:245–53.Search in Google Scholar
12. Reyaz Ahmed, AA, Thanigaiarasu, S, Venkatraman, S, Srinivasan, E, Rathakrishnan, E. Study of slanted perforated shapes in tabs for control of subsonic jets. In: 33rd AIAA applied aerodynamics conference. Dallas, TX: Aerospace Research Central; 2015:2423 p.10.2514/6.2015-2423Search in Google Scholar
13. Jyothy, VM, Wessley, GJJ, Solomon, AB. Study of wedge-shaped jet tabs for effective thrust vector control in supersonic vehicles. Adv Aircraft Spacecraft Sci 2023;10:342–55.10.1615/TFEC2023.ahp.046347Search in Google Scholar
14. Kumar, SS, Soltani, MR, Maghrebi, MJ. Design, analysis, and fabrication of a rocket simulator prototype for thrust vectoring stabilization. Aero Sci Technol 2020;98:105694. https://doi.org/10.1016/j.ast.2020.105694.Search in Google Scholar
15. Jayaprakash, S, Thanigaiarasu, S, Rathakrishnan, E. Numerical investigation of supersonic jet control using mechanical tabs. AIAA J Propul Power 2017;33:1029–42.Search in Google Scholar
16. Kumar, A, Singh, R, Sharma, P. Experimental analysis of jet tab effectiveness in thrust vector control systems. Int J Aerospace Eng 2018;2018:1.Search in Google Scholar
© 2025 Walter de Gruyter GmbH, Berlin/Boston
