Numerical Simulation of the Effect of Swing Center on a Supersonic Split Line Nozzle
A numerical investigation was performed in the present work to uncover the effect of swing center on a supersonic split line nozzle. Detailed nozzle internal flow and thrust performance were analysed, for serval swing center positions. It is found that, the step formed by the nozzle swing causes a b...
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| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | zho |
| Published: |
China Astronautic Publishing CO., LTD. ; Editorial Office of Physics of Gases
2025-07-01
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| Series: | 气体物理 |
| Subjects: | |
| Online Access: | http://qtwl.xml-journal.net/cn/article/doi/10.19527/j.cnki.2096-1642.1134 |
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| Summary: | A numerical investigation was performed in the present work to uncover the effect of swing center on a supersonic split line nozzle. Detailed nozzle internal flow and thrust performance were analysed, for serval swing center positions. It is found that, the step formed by the nozzle swing causes a bow shock to form upstream of the split line, whose distance travelling upstream increases approximately linearly with the increase of the swing angle, and a rapid trend results from the swing center moving upstream. The bow shock is regularly reflected on the wall, with the increase of the swing angle, resulting in significant attenuation of the amplification factor. However, for the nozzle with swing centers 10 mm and 15 mm upstream of the throat, the change from regular reflection to Mach reflection reduces the number of shock waves in the movable part of the nozzle, resulting in the amplification factor increase at swing angles of 8° and 10°. The linear relationship between the bow shock and the step height formed by the swing is always obvious. The bow shock forms Mach reflection, with the step height of 4.95 mm or more. For the nozzle with any swing center and swing angle, the linear relationship can be used to quickly estimate the position of the bow shock, and further predict the shock wave reflection type and the flow state in the nozzle. |
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| ISSN: | 2096-1642 |