Study on the Aerodynamic Performance of Novel Bypass Shock-Induced Thrust Vector Nozzle
This article studies the aerodynamic performance of a novel bypass shock-induced thrust vector nozzle. An arc-shaped bypass is innovatively designed to optimize nozzle performance and equips a variable shrinkage part. The nozzle performance is investigated numerically under diverse shrinkage area ra...
| Main Authors: | , , , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Isfahan University of Technology
2023-01-01
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| Series: | Journal of Applied Fluid Mechanics |
| Subjects: | |
| Online Access: | https://www.jafmonline.net/article_2179_bc962ffda3c200cd6cf6197e1565c97b.pdf |
| _version_ | 1828041000138833920 |
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| author | K. Wu Z. Liu R. Deng G. Zhang Z. Zhu V. R. P. Sethuraman X. Su |
| author_facet | K. Wu Z. Liu R. Deng G. Zhang Z. Zhu V. R. P. Sethuraman X. Su |
| author_sort | K. Wu |
| collection | DOAJ |
| description | This article studies the aerodynamic performance of a novel bypass shock-induced thrust vector nozzle. An arc-shaped bypass is innovatively designed to optimize nozzle performance and equips a variable shrinkage part. The nozzle performance is investigated numerically under diverse shrinkage area ratios. Computational results indicate that both geometry and friction choking have important effects on the nozzle performance. Normally, in the case of without any bypass shrinkage, the flow choking occurs at the bypass outlet. Very small bypass shrinkage is unable to change the flow choking location. The bypass geometry choking comes up at its throat as the shrinkage area ratio of the bypass reaches 0.06. According to computational results, the vectoring angle diminishes with the increasing shrinkage area ratio of the bypass, thrust force ratio, thrust efficiency, specific impulse ratio, and coefficient of discharge increase. As the NPR enlarges, the deflection angle and thrust efficiency decrease, and the thrust force ratio increases. |
| first_indexed | 2024-04-10T17:04:04Z |
| format | Article |
| id | doaj.art-5fa3b1aaabd940bebf9e3c50331f4513 |
| institution | Directory Open Access Journal |
| issn | 1735-3572 1735-3645 |
| language | English |
| last_indexed | 2024-04-10T17:04:04Z |
| publishDate | 2023-01-01 |
| publisher | Isfahan University of Technology |
| record_format | Article |
| series | Journal of Applied Fluid Mechanics |
| spelling | doaj.art-5fa3b1aaabd940bebf9e3c50331f45132023-02-06T07:55:54ZengIsfahan University of TechnologyJournal of Applied Fluid Mechanics1735-35721735-36452023-01-0116476577710.47176/jafm.16.04.15662179Study on the Aerodynamic Performance of Novel Bypass Shock-Induced Thrust Vector NozzleK. Wu0Z. Liu1R. Deng2G. Zhang3Z. Zhu4V. R. P. Sethuraman5X. Su6Key Laboratory of Fluid Transmission Technology of Zhejiang Province, Zhejiang Sci-Tech University, Hangzhou, Zhejiang Province, 310018, ChinaKey Laboratory of Fluid Transmission Technology of Zhejiang Province, Zhejiang Sci-Tech University, Hangzhou, Zhejiang Province, 310018, ChinaDepartment of Control Science and Engineering, Tongji University, Shanghai, 200092, ChinaKey Laboratory of Fluid Transmission Technology of Zhejiang Province, Zhejiang Sci-Tech University, Hangzhou, Zhejiang Province, 310018, ChinaKey Laboratory of Fluid Transmission Technology of Zhejiang Province, Zhejiang Sci-Tech University, Hangzhou, Zhejiang Province, 310018, ChinaDepartment of Aerospace System Engineering, Sejong University, Seoul, 05006, South KoreaKey Laboratory of Fluid Transmission Technology of Zhejiang Province, Zhejiang Sci-Tech University, Hangzhou, Zhejiang Province, 310018, ChinaThis article studies the aerodynamic performance of a novel bypass shock-induced thrust vector nozzle. An arc-shaped bypass is innovatively designed to optimize nozzle performance and equips a variable shrinkage part. The nozzle performance is investigated numerically under diverse shrinkage area ratios. Computational results indicate that both geometry and friction choking have important effects on the nozzle performance. Normally, in the case of without any bypass shrinkage, the flow choking occurs at the bypass outlet. Very small bypass shrinkage is unable to change the flow choking location. The bypass geometry choking comes up at its throat as the shrinkage area ratio of the bypass reaches 0.06. According to computational results, the vectoring angle diminishes with the increasing shrinkage area ratio of the bypass, thrust force ratio, thrust efficiency, specific impulse ratio, and coefficient of discharge increase. As the NPR enlarges, the deflection angle and thrust efficiency decrease, and the thrust force ratio increases.https://www.jafmonline.net/article_2179_bc962ffda3c200cd6cf6197e1565c97b.pdfaerodynamicsaeronauticssupersonic nozzleshock-induced thrust vector controlflow control |
| spellingShingle | K. Wu Z. Liu R. Deng G. Zhang Z. Zhu V. R. P. Sethuraman X. Su Study on the Aerodynamic Performance of Novel Bypass Shock-Induced Thrust Vector Nozzle Journal of Applied Fluid Mechanics aerodynamics aeronautics supersonic nozzle shock-induced thrust vector control flow control |
| title | Study on the Aerodynamic Performance of Novel Bypass Shock-Induced Thrust Vector Nozzle |
| title_full | Study on the Aerodynamic Performance of Novel Bypass Shock-Induced Thrust Vector Nozzle |
| title_fullStr | Study on the Aerodynamic Performance of Novel Bypass Shock-Induced Thrust Vector Nozzle |
| title_full_unstemmed | Study on the Aerodynamic Performance of Novel Bypass Shock-Induced Thrust Vector Nozzle |
| title_short | Study on the Aerodynamic Performance of Novel Bypass Shock-Induced Thrust Vector Nozzle |
| title_sort | study on the aerodynamic performance of novel bypass shock induced thrust vector nozzle |
| topic | aerodynamics aeronautics supersonic nozzle shock-induced thrust vector control flow control |
| url | https://www.jafmonline.net/article_2179_bc962ffda3c200cd6cf6197e1565c97b.pdf |
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