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Model for Asymmetry of Shock/Boundary Layer Interactions in Nozzle Flows

机译:喷嘴流中冲击/边界层相互作用的不对称模型

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摘要

The reason for the asymmetry phenomenon of shock/boundary layer interactions(SBLI)in a completely symmetric nozzle with symmetric flow conditions is still an open question.A model for the asymmetry of nozzle flows was proposed based on the properties of fluid entrainment in the mixing layer and momentum conservation. The asymmetry model is deduced based on the nozzle flow with restricted shock separation,and is still applicable for free shock separation.Flow deflection angle at nozzle exit is deduced from this model.Steady numerical simu-lations are conducted to model the asymmetry of the SBLIs in a planar convergent-divergent nozzle tested by previ-ous researchers.The obtained values of deflection angle based on the numerical results of forced symmetric nozzle flows can judge the asymmetry of flows in a nozzle at some operations.It shows that the entrainment of shear layer on the separation induced by SBLTs is one of the reasons for the asymmetry in the confined SBLIs.
机译:具有对称流动条件的完全对称喷嘴中的冲击/边界层相互作用(SBLI)的不对称现象的原因仍然是一个打开的问题。基于混合中的流体夹带的性质提出了喷嘴流动的不对称模型层和动量保护。基于喷嘴流动推导出具有限制性冲击分离的喷嘴流动,并且仍然适用于自由休克分离。从该模型推导出喷嘴出口处的挠曲角度。进行了数值数值,以模拟Sblis的不对称性。在由预防研究人员测试的平面趋同 - 发散喷嘴中。基于强制对称喷嘴流动的数值结果获得的偏转角值可以在一些操作中判断喷嘴中流动的不对称性。表明剪切的夹带Sblts诱导的分离层是限制Sblis中不对称的原因之一。

著录项

  • 来源
    《南京航空航天大学学报(英文版)》 |2018年第1期|146-153|共8页
  • 作者

    Wang Chengpeng; Zhuo Changfei;

  • 作者单位

    College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,P.R.China;

    Department of Aerospace Engineering,Nanjing University of Science and Technology,Nanjing 210094,P.R.China;

  • 收录信息 中国科学引文数据库(CSCD);中国科技论文与引文数据库(CSTPCD);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 计算空气动力学;
  • 关键词

  • 入库时间 2022-08-18 02:00:59
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