| 变比热对超燃冲压发动机尾喷管设计的影响分析 |
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| 引用本文： | 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(2):43-47. |
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| 作者姓名： | 王玉峰 吴宝元 王东东 |
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| 作者单位： | 西安航天动力研究所,陕西,西安710100 |
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| 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。
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| 关 键 词： | 超燃冲压发动机 尾喷管 变比热 |
Scramjet engine nozzle design with variable specific heat |
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| Wang Yufeng,Wu BaoYuan,Wang Dongdong.Scramjet engine nozzle design with variable specific heat[J].Journal of Rocket Propulsion,2010,36(2):43-47. |
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| Authors: | Wang Yufeng Wu BaoYuan Wang Dongdong |
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| Institution: | (Xi＇an Aerospace Propulsion Institute, Xi＇an 710100, China) |
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| 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. |
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| Keywords: | scramjet engine nozzle variable specific heat |
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