| 摘要: |
| 为了简化燃烧室流场模拟,提高内外流场数值仿真效率,为高超声速飞行器一体化构型提供设计依据和参考,发展了一种在流动控制方程组中加入源项的数值模拟方法。通过调节源项作用位置及大小,该方法可实现对超燃冲压发动机燃烧室内的添质添能流动的模拟。与直联式试车台实验数据对比表明,该方法能够较好地模拟冲压发动机内压力分布,能够满足飞行器气动/推进一体化构型方案设计及总体方案设计阶段的需求。 |
| 关键词: 高超声速飞行器 超燃冲压发动机+ 一体化 数值仿真 源项法+ |
| DOI： |
| 分类号:V231; |
| 基金项目: |
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| Simplified numerical simulation method for integrated flow field of hypersonic vehicle |
|
FAN Xiao-qiang, JIA Di, PAN Sha, LI Hua
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Inst.of Aerospace and Material Engineering,National Univ.of Defence Technology,Changsha 410073,China
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| Abstract: |
| A source term method is developed to simulate the flow field of scramjet combustion chamber.By configuring the value and adding position of the source term,the flow field of the combustor can be calculated.Numerical result using the source term method is compared to the experiment data acquired on direct connected scramjet test facility.The comparison indicates that the source term method can predict pressure distribution of the combustor and can meet the need of the vehicle configuration and integral design. |
| Key words: Hypersonic vehicle Scramjet~+ Integration Numerical simulation Source term method~+ |
