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超声速混合层发展情况的非线性时间序列分析 被引量:1

Non-linear Time Series Analysis of Evolution Status of Supersonic Mixing Layer
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摘要 采用大涡模拟数值方法,模拟了具有工程应用背景的二维超声速湍流混合层,通过非线性时间序列分析伪相图、关联维数和Lyapunov指数,得到了混合层发展情况的混沌特性。结果表明,混合层中心线沿流向位置的压力伪相图可定性地表示混合层的稳定性,关联维数分布可定量描述混合层经历的线性失稳、非线性失稳和涡合并阶段等发展情况,最大Lyapunov指数分布作为关联维数分析结果的验证。对于相应的超声速混合层实验,采用非线性时间序列分析方法研究混合层发展情况具有通用性。 Coherent structures of two-dimensional supersonic turbulent mixing layer with engineering background are investigated by using the method of Large Eddy Simulation (LES). Chaos characteristics of evolution status are obtained by the non-linear time series analysis of pseudo-phase portrait, Lyapunov exponent and correlation dimension. The results show that the pseudo-phase portrait of pressure can denote the stability of mixing layer. The distribution of correlation dimensions can be used to measure the evolution status of mixing layer quantificationally, and the distribution of maximal Lyapunov exponents can be used to validate the measure results above. In corresponding experiments for mixing layer, the universality of studies on evolution status of mixing layer by the method of non-linear time series analysis is testified.
出处 《国防科技大学学报》 EI CAS CSCD 北大核心 2009年第5期112-119,共8页 Journal of National University of Defense Technology
基金 国家部委基金资助项目
关键词 超声速混合层 大涡模拟 非线性时间序列 混沌 supersonic mixing layer large eddy simulation non-linear time series chaos
作者简介 于江飞(1984-),男,博士生。
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  • 1刘敬华,凌文辉,胡欲立,刘兴洲,于守志.亚/超双模态超音速燃烧的实验研究[J].推进技术,1996,17(2):48-52. 被引量:5
  • 2谭慧俊,郭荣伟.高超声速混合模块冲压发动机亚燃模块进气道的高焓风洞试验研究[J].航空学报,2007,28(4):783-790. 被引量:15
  • 3张涵信.无波动、无自由参数的耗散差分格式[J].空气动力学学报,1988,7(2):1431-165.
  • 4Mercier Robert, McClinton C. Hypersonic propulsion transforming the future of flight[R]. AIAA 2003-2732.
  • 5Kiersey J L. Airbreathing propulsion for defense of the surface fleet[R]. Johns Hopkins APLTechnical Digest, 1992, 13: 57q58.
  • 6Waltrup P J. Hypersonic airbreathing propulsion: Evolution and opportunities[R]. AGARD CP 428, 1987-04:12.
  • 7Waltrup P J. The dual combustor ramjet: a versatile propulsion system for tactical missile applications[R]. AGARD CP-726, 1992-03:7.
  • 8Waltrup Paul J, et al. History of ramjet and scramjet propulsion development for U.S. Navy missiles[J]. Johns Hopkins APL Technical Digest, 1997,18(2).
  • 9Billig F S, Waltrup P J, Stockbridge R D. Integral-rocket dual-combustior ramjets: a new propulsion concept[J]. Journal of Spacecraft and Rockets 1980(5).
  • 10Situ M, Wang C, Lu H P. Hot gas piloted energy for supersonic combustion of kerosne with dual-cavity[R]. AIAA 2001-0523.

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  • 1K M Smith,J C Dutton. Investigation of large-scale struc- tures in supersonic planar base flows [ J]. AIAA Journal, 1996,34(6) : 1146 - 1152.
  • 2刘或.双燃烧室冲压发动机混合增强及燃烧流场的实验和数值仿真研究[D].长沙:国防科学与技术大学,2009.
  • 3D W Bogdanoff. Compressibility effects in turbulent shear layers[J]. AIAA .lournal, 1983, 21(6) :926 -927.
  • 4Clemens N T, Mangal G M. Two- and three-dimensional effects in the supersonic mixing layer[ J] . AIAA Journal, 1992,30(4) : 973 -981.
  • 5Elliott G S, Samimy M, Arnette S A. Study of compressible mixing layers using filtered Rayleigh scattering based visu- alizations [ J ]. AIAA Journal, 1992, 30 ( 10 ) : 2567 - 2569.
  • 6Goebel S G,Dutton J C. Experimental study of compressible turbulent mixing layers[ J]. AIAA Journal, 1991,29 (4) : 538 - 546.

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