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二维进气道不启动流场非定常特性的混合LES/RANS模拟

陈逖 刘卫东 范晓樯

陈逖, 刘卫东, 范晓樯. 二维进气道不启动流场非定常特性的混合LES/RANS模拟[J]. 航空动力学报, 2012, 27(8): 1792-1800.
引用本文: 陈逖, 刘卫东, 范晓樯. 二维进气道不启动流场非定常特性的混合LES/RANS模拟[J]. 航空动力学报, 2012, 27(8): 1792-1800.
CHEN Ti, LIU Wei-dong, FAN Xiao-qiang. Investigation on unsteady characteristics of unstarted two-dimensional inlet flow using hybrid LES/RANS method[J]. Journal of Aerospace Power, 2012, 27(8): 1792-1800.
Citation: CHEN Ti, LIU Wei-dong, FAN Xiao-qiang. Investigation on unsteady characteristics of unstarted two-dimensional inlet flow using hybrid LES/RANS method[J]. Journal of Aerospace Power, 2012, 27(8): 1792-1800.

二维进气道不启动流场非定常特性的混合LES/RANS模拟

基金项目: 国家自然科学基金(10802096)

Investigation on unsteady characteristics of unstarted two-dimensional inlet flow using hybrid LES/RANS method

  • 摘要: 采用一种混合大涡模拟/雷诺平均Navier-Stokes(LES/RANS)方程模拟方法结合5阶WENO(weighted essentially non-oscillatory)格式对马赫数为3的来流中、内收缩比为1.5的不启动状态下的二维进气道进行了计算,再现了不启动进气道中的非定常流场.计算结果表明:所采用的模拟方法对入口处的平均绝热壁温、摩擦速度和雷诺应力的计算精度较好,进气道不启动流场中激波波系和分离区存在大时空尺度的低频运动,其占主导的特征频率和典型的激波/湍流边界层干扰问题中激波和分离区的低频频率接近,且进气道出现了间歇性的启动状态.

     

  • [1] 王翼.高超声速进气道启动问题研究 .长沙:国防科学技术大学,2009. WANG Yi.Investigation on the starting characteristics of hypersonic inlet .Changsha:National Universoty of Defense Technology,2009.(in Chinese)
    [2] Dolling D S.Fifty years of shock wave/boundary-layer interaction reasearch:what next?[J].AIAA Journal,2001,39(8):1517-1531.
    [3] Knight D,Yan H,Panaras A,et al.Advances in CFD prediction of shock wave turbulent boundary layer interactions .AIAA Paper 2002-0437,2002.
    [4] Knight D,Degrez G.Shock wave boundary layer interactions in high mach number flows:a critical survey of current CFD prediction capabilities .AGARD Report Advisory Report AR-319,1998.
    [5] Zheltovodov A,Borisov A,Knight D,et al.The possibilities of numerical simulation of shock wave/boundary layer interaction in supersonic and hypersonic flows //Proceedings of the International Conference on the Methods of Aerophysical Research.Siberian Division,Novosibirsk,Russia:Institute of Theoretical and Applied Mechanics,Russian Academy of Sciences,1992:164-170.
    [6] Loginov M S,Adams N A,Zheltovodov A A, et al.Large eddy simulation of turbulent boundary layer interaction with successive shock and expansion waves //Proceedings of the International Conference on the Methods of Aerophysical Research.Novosibirsk,Russia:Publishing House Nonparel,2004:149-157.
    [7] Adams N.Direct simulation of the turbulent boundary layer along a compression ramp at M =3 and Re =1685[J].Journal of Fluid Mech.,2000,420(1):47-83.
    [8] Rizzetta D,Visbal M.Large eddy simulation of supersonic compression ramp flow .AIAA 2001-2858,2001.
    [9] Frohlich J,Von Terzi D.Hybrid LES/RANS methods for the simulation of turbulent flows[J].Progress in Aerospace Sciences,2008,44(5):349-377.
    [10] Xiao X D,Edwards J R,Hassan H A.Inflow boundary conditions for LES/RANS simulations with applications to shock wave/boundary layer interactions .AIAA Paper 2003-79,2003.
    [11] Strelets M.Detached eddy simulation of massively separated flows .AIAA Paper 2001-0879,2001.
    [12] Edwards J R,Choi J I,Boles J A.Large eddy/Reynolds-averaged Navier-Stokes simulation of a Mach 5 compression-corner interaction[J].AIAA Journal,2008,46(4):977-991.
    [13] Menter F R.Two-equation eddy-viscosity turbulence models for engineering applications[J].AIAA Journal,1994,32(8):1598-1605.
    [14] Lenormand E,Sagaut P,Comte P,et al.Sub-grid scale models for large-eddy simulations of compressible,wall-bounded flows[J]. AIAA Journal,2000,38(8):1340-1350.
    [15] Edwards J R.A Low-diffusion fluxing-splitting scheme for Navier-Stokes calculations[J].Computer & Fluids,1997,26(6):635-659.
    [16] Jiang G,Shu C W.Efficient implementation of weighted ENO schemes[J].Journal of Computational Physics,1996,126(1):917-923.
    [17] Dubuc L,Cantariti F,Woodgate M,et al.Solution of unsteady Euler equations using an implicit dual-time step method[J].AIAA Journal,1998,36(8):1417-1424.
    [18] Jameson A,Yoon S.Lower-upper implicit schemes with multiple grids for the Euler equations[J].AIAA Journal,1987,25(7):929-935.
    [19] 陈逖,刘卫东,范晓樯,等.“回收/调节”方法在混合LES/RANS模拟方法中的应用[J].航空动力学报,2011,26(6):1215-1222. CHEN Ti,LIU Weidong,FAN Xiaoqiang,et al.Application of recycling/rescaling method in hybrid LES/RANS simulation method[J].Journal of Aerospace Power,2011,26(6):1215-1222.(in Chinese)
    [20] Boles J A,Choi J I,Edwards J R,et al.Multi-wall recycling/rescaling method for inflow turbulence generation .AIAA Paper 2010-1099,2010.
    [21] Smits A J,Dussauge J P.Turbulent shear layers in supersonic flow[M].2nd ed.New York,USA:Springer Science and Business Media,1996.
    [22] Coles D.Measurements in thr boundary layer on a smooth flat plate in supersonic flow .NASA Reports,JPL-20-70,1953.
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出版历程
  • 收稿日期:  2011-09-22
  • 刊出日期:  2012-08-28

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