航天推进技术研究院主办
[1]柳长安,邹宇.环喉型塞式喷管的数值仿真研究[J].火箭推进,2010,36(06):1-5.
Numerical simulation of an annular throat plug nozzle[J].Journal of Rocket Propulsion,2010,36(06):1-5.
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Numerical simulation of an annular throat plug nozzle[J].Journal of Rocket Propulsion,2010,36(06):1-5.
环喉型塞式喷管的数值仿真研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
36
期数:
2010年06期
页码:
1-5
栏目:
研究与设计
出版日期:
2010-12-15
- Title:
- Numerical simulation of an annular throat plug nozzle
- 文章编号:
- 1672-9374(2010)06-0001-05
- 分类号:
- V430
- 文献标志码:
- A
- 摘要:
- 通过流场数值仿真计算方法对环喉型塞式喷管进行了研究，对比计算了不同外流条件下塞式喷管的流场结构和性能。分析表明该塞式喷管的结构方案独特，具有稳定的高空高速性能，与传统的钟型喷管相比低空性能更优异。
- Abstract:
- An annular throat plug nozzle is studied by the calculation method of flow-field numerical simulation. The flow-field structures and the characters of the plug nozzle under the condition of different freestreams are compared and calculated. The structure design of the plug nozzle is unique. The analysis shows that the plug nozzle has stable performance at high altitude and high speed, and has more excellent
参考文献/References:
[1] IMMICH H, NASUTI F, ONOFRI M, et al. Experimental
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备注/Memo
收稿日期：2010-０8-05；修回日期：2010-0８-2７
基金项目：国家航天技术支撑项目
作者简介： 柳长安（1974—），男，博士，研究领域为液体火箭发动机总体设计
更新日期/Last Update:
1900-01-01