Volume 26 Issue 4
Apr.  2011
Turn off MathJax
Article Contents
ZHAO Hui-yong, LEI Bo, LE Jia-ling. Numerical application of nonlinear EASM model to the interaction between shock waves /turbulent boundary layer[J]. Journal of Aerospace Power, 2011, 26(4): 860-866.
Citation: ZHAO Hui-yong, LEI Bo, LE Jia-ling. Numerical application of nonlinear EASM model to the interaction between shock waves /turbulent boundary layer[J]. Journal of Aerospace Power, 2011, 26(4): 860-866.

Numerical application of nonlinear EASM model to the interaction between shock waves /turbulent boundary layer

  • Received Date: 2010-03-22
  • Rev Recd Date: 2010-12-30
  • Publish Date: 2011-04-28
  • The nonlinear explicit algebraic stress model (EASM) in k-ω form was used to compute the interaction between shock wave and turbulent boundary layer of supersonic cavity,compression corner and simplified model of side-compression inlet which are usually used in scramjet engine.The main focus was computational resolution of EASM model on wall pressure,friction,Stanton number and skin friction lines.The computational results of EASM model were compared with those of SST (shear stress transport) model.EASM model has better computational resolution on wall pressure,friction and Stanton number so that it can be generalized.EASM model is better than SST model in computation of Stanton number and skin friction lines.

     

  • loading
  • [1]
    Rumsey C L,Gatski T B.Summary of EASM turbulence models in CFL3D with validation test cases .NASA TM 2003-212431,2003.
    [2]
    Baurle R A.Modeling of high speed reacting flows:established practices and future challenges .AIAA Paper 2004-0267,2004.
    [3]
    Kral L D,Recent experience with different turbulence models applied to the calculation of flow over aircraft components[J].Progress in Aerospace Sciences,1998,34(7):481-541.
    [4]
    Georgiadis N J,Papamoschou D.Computational investigation of high-speed dual-stream jets .AIAA Paper 2003-3311,2003.
    [5]
    赵慧勇,雷波,乐嘉陵.非对称交叉激波和湍流边界层相互作用的数值研究[J].航空动力学报,2009,24(10):2183-2188. ZHAO Huiyong,LEI Bo,LE Jialing.Numerical investigation of interaction between asymmetric crossing shock waves/turbulence boundary layer[J].Journal of Aerospace Power,2009,24(10):2183-2188.(in Chinese)
    [6]
    Menter F R.Zonal two-equation k-ω turbulence models for aerodynamic flows .AIAA Paper 93-2906,1993.
    [7]
    Settles G S,Williams D R,Baca B K,et al.Reattachment of a compressible turbulent free shear layer[J].AIAA Journal,1982,20(1):60-67.
    [8]
    Delery J,Panaras A G.Shock-wave/boundary layer interactions in high Mach number flows:in hypersonic experimental and computational capability,improvement and validation,volume 1 .AGARD AR 319,1996.
    [9]
    Zheltovodov A A,Maksimov A I,Schulein E,et al.Experimental and computational studies of crossing-shock-wave/turbulence-boundary-layer interaction .Proceedings of International Conference RDAMM-2001,2001,6(2):153-162.
    [10]
    Thivet F,Knight D D,Zheltovodov A A,et al.Some insights in turbulence modeling for crossing-shock-wave/boundary-layer interactions .AIAA Paper 2000-0131, 2000.
    [11]
    Langtry R B,Menter F R.Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes[J].AIAA Journal,2009,47(12):2894-2906.
    [12]
    WANG Liang,FU Song.Modeling flow transition in a hypersonic boundary layer with Reynolds-averaged Navier-Stokes approach[J].Science in China,Series G:Physics,Mechanics and Astronomy,2009,52(5):768-774.
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Article Metrics

    Article views (1669) PDF downloads(14) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return