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超声速流中激波/湍流附面层干扰数值模拟
引用本文:雷雨冰,梁德旺,黄国平.超声速流中激波/湍流附面层干扰数值模拟[J].南京航空航天大学学报,2004,36(1):1-5.
作者姓名:雷雨冰  梁德旺  黄国平
作者单位:南京航空航天大学能源与动力工程学院,南京,210016
摘    要:采用修正的B/L湍流模型以及多块结构化网格求解了二维N-S方程。分别对超声速流和高超声速流中的激波/湍流附面层干扰进行了数值研究。本文首先研究了进口马赫数为2.96的超声速流。计算结果准确预测了入射斜激波在平直壁面引起湍流附面层分离的流动特征:分离点的反射激波、分离包引起的膨胀扇以及再附点的反射激波。计算的壁面压力分布与实验值吻合较好,计算的分离区长度与实验值比较有一定误差。本文还对进口马赫数为9.22的高超声速流中压缩角引起的激波/湍流附面层干扰进行了数值研究。计算结果与实验结果吻合较好。

关 键 词:超声速流  激波  湍流附面层  干扰  数值模拟  飞行器
文章编号:1005-2615(2004)01-0001-05
修稿时间:2003年6月27日

Numerical Study of Shock Wave/Turbulent Boundary Layer Interaction in Supersonic Flows
LEI Yu-bing,LIANG De-wang,HUANG Guo-ping.Numerical Study of Shock Wave/Turbulent Boundary Layer Interaction in Supersonic Flows[J].Journal of Nanjing University of Aeronautics & Astronautics,2004,36(1):1-5.
Authors:LEI Yu-bing  LIANG De-wang  HUANG Guo-ping
Abstract:Two-dimensional N-S equation with modified B/L turbul ent model in multi-block structured grids is solved to simulate shock wave/turbulent boundary layer interactions. In an oncoming flow at Mach number 2 96, the calculational results predict well the flow characteristics of t urbulent boundary layer separation induced by incident shock wave: a separation shock fo llowed by expansion fan around separation bubble and shock in reattachment point . A good agreement in wall pressure distribution is reached between numerical ca lculation and the experiment. Shock wave/turbulent boundary layer interaction i n hypersonic compression-corner flows at Mach number 9 22 is also studied, and the calculational results are consistent with experimental data.
Keywords:shock wave/turbulent boundary layer interaction  supersonic flow  numerical calculation  separated flow  adverse pressure gradi ent
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