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[1]王玉峰,吴宝元,王东东.变比热对超燃冲压发动机尾喷管设计的影响分析[J].火箭推进,2010,36(02):43-47.
　Wang Yufeng,Wu BaoYuan,Wang Dongdong.Scramjet engine nozzle design with variable specific heat[J].Journal of Rocket Propulsion,2010,36(02):43-47.
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变比热对超燃冲压发动机尾喷管设计的影响分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 36 期数: 2010年02期 页码: 43-47 栏目: 研究与设计 出版日期: 2010-04-15
Title:
Scramjet engine nozzle design with variable specific heat
文章编号:
(2010)02-0043-0５
作者:
王玉峰; 吴宝元; 王东东
西安航天动力研究所，陕西，西安 710100
Author(s):
Wang Yufeng;  Wu BaoYuan;  Wang Dongdong
Xi'an Aerospace Propulsion Institute, Xi'an 710100, China
关键词:
超燃冲压发动机; 尾喷管; 变比热
分类号:
V439
文献标志码:
A
摘要:
当气体总温较高时，气体的比热比将不再保持不变，而是温度的函数。由于超燃发动机尾喷管的入口温度很高，因此，在喷管型面设计时应该考虑比热变化对型面产生的影响。给出了基于量热完全气体模型和热完全气体模型的超燃冲压发动机尾喷管设计方法。并比较了比热比不变和比热比随气体温度变化时对喷管型面设计的影响。对量热完全气体的应用限制进行了初步讨论。
Abstract:
When the gas stagnation temperature increases, the specific heat ratio starts to vary with the temperature. Scramjet engine nozzle inlet temperature is very high and the influence of specific heat variation must be taken into account. This paper describes a method for scramjet engine nozzle design. A comparison between calorically perfect gas and that of thermally perfect gas is given.

参考文献/References:

[1]潘锦珊. 气体动力学基础[M]. 北京: 北京航空航天大学出版社, 1999. [2]Toufik Zebbiche. SuperSonic Two-Dimensional Minimum Length Nozzle Design at High Temperature[J]. Application for Air. 2006, (3): 29-38. [3]王新月, 杨振鹏. 化学非平衡流动对超燃冲压发动机尾喷管性能的影响[J]. 航空动力学报, 2009, 20(5): 1023-1027. [4]李建平. 超燃冲压发动机尾喷管设计方法研究[J]. 长春理工大学学报, 2007, 30(1): 114-116. [5]徐惊雷. 超燃冲压发动机非对称喷管非设计状态性能计算[J]. 推进技术, 2007, 28(3): 287-290. [6]张艳惠. 超燃冲压发动机非对称喷管设计点性能[J]. 推进技术, 2007, 28(3): 282-286. [7]Nickerson G R. Optimized Supersonic Exhaust Nozzles for Hypersonic Propulsion[R]. AIAA 88-3161. [8]王一白. 瓦状塞式喷管的设计和试验分析[J]. 火箭推进, 2008, 34(1): 1-6.

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备注/Memo

收稿日期：200９-10-１5；修回日期：200９-11-1７。
作者简介： 王玉峰（1980—），男，硕士，研究领域为冲压发动机系统设计。

更新日期/Last Update: 1900-01-01