| 二元混压超音速进气道湍流流场数值模拟 |
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| 引用本文： | 李进贤,王国辉,高朝辉,蔡体敏,郭颜红,蔡选义.二元混压超音速进气道湍流流场数值模拟[J].固体火箭技术,2000,23(2):16-20. |
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| 作者姓名： | 李进贤 王国辉 高朝辉 蔡体敏 郭颜红 蔡选义 |
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| 作者单位： | 1. 西北工业大学航天工程学院,西安,710072
2. 中国航空工业总公司第014中心,洛阳,471009 |
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| 摘 要： | 对二元混压超音速进气道湍流流场进行了数值模拟。计算中将无波动无自由参数耗散差分格式与对流迎风矢通量分裂技术耦合使用，应用Ｂａｌｄｗｉｎ－Ｌｏｍａｘ代数湍流模型，按照ＭａｃＣｏｒｍａｃｋ时间分裂方法对贴体坐标系下二维雷诺平均Ｎ－Ｓ方程进行差分离散，模拟了二元混压超音速进气道在临界和非临界流动状态下整个流场的流动情况。进气道主要部分的计算结果与理论分析相一致。
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| 关 键 词： | 冲压喷气发动机 超音速进气道 数值模拟 |
Numerical Simulation of Turbulent Flow in 2-D Mixed-Compression Supersonic Inlet |
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| LI Jin-xian,WANG Guo-hui,GAO Zhao-hui,CAI Ti-min,GUO Yan-hong,CAI Xuan-yi.Numerical Simulation of Turbulent Flow in 2-D Mixed-Compression Supersonic Inlet[J].Journal of Solid Rocket Technology,2000,23(2):16-20. |
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| Authors: | LI Jin-xian WANG Guo-hui GAO Zhao-hui CAI Ti-min GUO Yan-hong CAI Xuan-yi |
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| Abstract: | The turbulent flow in 2 D mixed compression supersonic inlet is simulated by numerical method.During the calculations,non oscillatory containing no free parameters and dissipative (NND) format and advection upstream splitting method (AUSM) are combined,and the Baldwin Lomax turbulent model and MacCormack time splitting method are applied to discrete the Reynold average Navier Stokes equation in two dimensinoal generalized coordinates with finite difference.Applying this algorithm,critical and non critical flow status of whole flow field are simulated in 2 D mixed compression supersonic inlet.The calculated results of inlet main portion are in accord with theoretical analysis. |
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| Keywords: | ramjet engine supersonic inlet numerical simulation NND format vector splitting technique |
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