期刊文献+

矩形喷管内外喷流流场的数值模拟 被引量:1

Numerical Simulation in Flow Fields of a Rectangular Nozzle
下载PDF
导出
摘要 基于 Frave 平均的 N S方程和 B/ L 湍流模型,采用了 Jam eson 格式和 M U S C L 格式,对外流在亚声、超声和零 M ach 数三种状态时矩形喷管的喷流流场进行了数值模拟,探讨了内外喷流及喷管内的流动特征,并与实验数据进行了比较,计算结果与实验结果吻合较好,验证了计算所使用的 N A P A 软件的可靠性,从而为用计算流体力学的方法模拟具有两股来流的三维湍流流场提供了一种有效的手段。 Based on Frave averaged three dimensional compressible Navier Stokes equations and Baldwin Lomax algebraic turbulence model, the jet flow field of a rectangular nozzle under the state of subsonic, supersonic and zero Mach number is simulated. The characteristics of the flow from inside and outside nozzle and jet flow are discussed and the numerical results are compared with experimental data. The comparison shows that they match well. It verified the reliability of the NAPA software used in the simulation, and so an effective method for simulating three dimensional turbulent flow field with two inflows by computational fluid mechanics is achieved.
作者 李博 梁德旺
出处 《南京航空航天大学学报》 EI CAS CSCD 北大核心 1999年第4期398-403,共6页 Journal of Nanjing University of Aeronautics & Astronautics
基金 国家教委优秀跨世纪人才基金 江苏省青蓝工程基金
关键词 流体力学 喷流 数值模拟 矩形喷管 fluid mechanics computation fluid mechanics jet stream numerical simulation
  • 相关文献

参考文献1

二级参考文献5

共引文献25

同被引文献20

  • 1伊赫桑·巴伦,陈乃良译.纯物质热化学数据手册[M].北京:科学出版社,2003.135,588
  • 2Lee Jinho, Ralph W, Buehrle R J. The GE-NASA RTA hyper burner design and development [R]. NASA/TM-2005-213803,2005.
  • 3Shaw R J,Peddie C L. Overview of NASA's UEET and TBCC/RTA programs [R]. NASA/CP-2003- 212458/VOL(1) ,2003.
  • 4Gamble E, Haid D. Improving off-design nozzle per- formance using fluidic injection [R]. AIAA 2004- 1206,2004.
  • 5Hendrick P, Saint-Mard M. ACES S/inger-type TS- TO family with common first stage[R]. AIAA 1998- 3229,1998.
  • 6Berens T M. Experimental and numerical analysis of a two duct nozzle/after body model at supersonic mach numbers[R] AIAA 1995-6085,1995.
  • 7Lederer R,Schwab R. Hypersonic air breathing pro- pulsion activities for S/inger[R]. AIAA 1991-5040, 1991.
  • 8Walker S, Tang Ming, Mamp|ata C. TBCC propul- sion for a mach 6 hypersonic airplane [R]. AIAA 2009-7238,2009.
  • 9Mizobata K,Kimura H,Sugiyama H. Conceptual de- sign of flight demonstrator vehicles for the ATREX engine[R]. AIAA 2003-7028,2003.
  • 10Isomura K, Omi J. A comparative study of an ATREX engine and a turbo jet engine [R]. AIAA2001-3239,2001.

引证文献1

二级引证文献4

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部