| 单模块超燃冲压发动机一体化流场数值计算 |
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| 引用本文： | 徐旭,蔡国飙.单模块超燃冲压发动机一体化流场数值计算[J].宇航学报,2004,25(1):114-118. |
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| 作者姓名： | 徐旭 蔡国飙 |
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| 作者单位： | 北京航空航天大学宇航学院,北京,100083 |
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| 基金项目： | 国家自然科学基金 (10 0 72 0 10 )，航空基金 (0 0 A5 10 70 )资助项目 |
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| 摘 要： | 采用数值计算方法求解了单模块超燃冲压发动机内外流一体化流场，得到了流场详细结构和单模块发动机的性能参数，并对不同工况下的发动机性能进行了对比研究，探讨了发动机在有、无进气道侧压情况下的性能差异，分析了其中的原因。计算结果表明，研究工作中所发展的数值计算软件可以用于超燃冲压发动机的一体化流场计算，正确给出发动机的各项性能。计算结果还显示了发动机设计模型中存在的不足。
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| 关 键 词： | 超燃冲压发动机 超声速燃烧 一体化流场计算 一体化设计 单模块 |
| 文章编号： | 1000-1328(2004)01-0114-05 |
Integrated flow field calculation of a modularized scramjet |
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| XU Xu,CAI Guo-biao HTSS.Integrated flow field calculation of a modularized scramjet[J].Journal of Astronautics,2004,25(1):114-118. |
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| Authors: | XU Xu CAI Guo-biao [HTSS] |
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| Institution: | XU Xu,CAI Guo-biao [HT6SS] |
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| Abstract: | An integrated scramjet flow field was numerically investigated using multi-species Navier-Stokes equations with finite rate chemistry.The Lower-Upper(LU) decomposition method was used to integrate the NS equations in time while the MUSCL type upwind scheme in space.The performances of the scramjet,including thrust coefficient,drag coefficient,lift coefficient and specific impulse were obtained from the computational results.Scramjet performances under different attack angles and gas-fuel equivalence ratios were studied,and the influence of inlet side compression on scramjet performances were investigated.It is shown that the codes developed in this work can be used to simulate the integrated flow field of scramjet.Some suggestions were given to improve the scramjet design model. |
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| Keywords: | Scramjet Supersonic combustion Integrated flow field calculation Integrated design |
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