Experimental study of jet-tab method with different tab lengths
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Manikandan Subramaniyan
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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.
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Research ethics: Not applicable.
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Informed consent: Informed consent was obtained from all individuals included in this study.
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Author contributions: All authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Use of Large Language Models, AI and Machine Learning Tools: None declared.
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Conflict of interest: The authors state no conflict of interes.
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Research funding: AR&DB (Aeronautical Research and Development Board) Project No – 1946.
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Data availability: Not applicable.
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