留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

有限振幅扰动下高超声速钝楔绕流感受性

唐小军 王振清 孟祥男 吕红庆

唐小军, 王振清, 孟祥男, 等 . 有限振幅扰动下高超声速钝楔绕流感受性[J]. 北京航空航天大学学报, 2014, 40(5): 675-684. doi: 10.13700/j.bh.1001-5965.2013.0330
引用本文: 唐小军, 王振清, 孟祥男, 等 . 有限振幅扰动下高超声速钝楔绕流感受性[J]. 北京航空航天大学学报, 2014, 40(5): 675-684. doi: 10.13700/j.bh.1001-5965.2013.0330
Tang Xiaojun, Wang Zhenqing, Meng Xiangnan, et al. Receptivity of hypersonic flow over blunt wedge under finite-amplitude disturbance wave[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(5): 675-684. doi: 10.13700/j.bh.1001-5965.2013.0330(in Chinese)
Citation: Tang Xiaojun, Wang Zhenqing, Meng Xiangnan, et al. Receptivity of hypersonic flow over blunt wedge under finite-amplitude disturbance wave[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(5): 675-684. doi: 10.13700/j.bh.1001-5965.2013.0330(in Chinese)

有限振幅扰动下高超声速钝楔绕流感受性

doi: 10.13700/j.bh.1001-5965.2013.0330
基金项目: 

国家自然科学基金资助项目(11272096);高等学校博士学科点专项科研基金资助项目(20112304110015);中央高校基本科研业务费资助项目(HEUCF130216)

详细信息
    作者简介:

    唐小军(1987- ),男,湖南祁阳人,博士生,tangxiaojun2214@163.com.

  • 中图分类号: O355;V211

Receptivity of hypersonic flow over blunt wedge under finite-amplitude disturbance wave

  • 摘要: 为了研究自由流脉冲波作用下高超音速流动感受性特征,采用高阶有限差分方法模拟钝楔超高音速绕流中来流慢声脉冲波作用下的非定常流场,并应用傅里叶频谱分析了边界层扰动模态的演化.结果显示,自由流脉冲扰动下,边界层不同模态波沿流线呈现不同变化规律.球头区边界层感受到的主要是基频波,在球头向非球头区过渡段,主导模态迅速向高频迁移;在非球头区,主导模态频率缓慢向高频迁移.总的来说,沿流向总扰动模态中的低频模态成分变小,高频,特别是二阶谐频附近模态成分显著地增大.沿流线发展,边界层不同扰动模态之间存在伴随能量迁移的模态竞争物理现象,主导模态的发展对其他模态有很强的抑制作用.

     

  • [1] Meyer B, Nelson H F,Riggins D.Hypersonic drag and heat-transfer reduction using a forward-facing jet[J].Journal of Aircraft,2001,38(4):680-686
    [2] Hayashi K, Aso S.A study on reduction of aerodynamic heating by opposing jet in supersonic flow[J].Journal of the Japan Society for Aeronautical and Space Sciences,2004,52:38-44
    [3] Venukumar B, Jagadeesh G,Reddy P J K.Counter flow drag reduction by supersonic jet for a blunt body in hypersonic flow[J].Physics of Fluids,2006,18(11):571-576
    [4] Finley P J. The flow of a jet from a body opposing a supersonic free stream[J].Journal of Fluid Mechanics,1966,26:337-368
    [5] 孙忠恕,温功碧. 运动突风作用下机翼-机身-尾翼亚音速非定常气动力数值计算[J].航空学报,1981,2(3):23-30 Sun Zhongshu,Wen Gongbi.Numerical computation of unsteady subsonic aerodynamic forces on wing-body-tail exposed to traveling gust[J].Acta Aeronautica et Astronautica Sinica,1981, 2(3): 23-30(in Chinese)
    [6] 王振清,唐小军, 孟祥男,等.钝锥高超音速绕流脉冲扰动研究[J].哈尔滨工程大学学报,2013,34(3):298-305 Wang Zhenqing,Tang Xiaojun,Meng Xiangnan,et al.Study on the effect of pulse perturbation in hypersonic flow over a blunt cone[J].Journal of Harbin Engineering University,2013, 34(3): 298-305(in Chinese)
    [7] 吴志刚,惠俊鹏, 杨超.高超声速下翼面的热颤振工程分析[J].北京航空航天大学学报,2005,31(3):270-273 Wu Zhigang,Hui Junpeng,Yang Chao.Hypersonic aerothermoelastic analysis of wings[J].Journal of Beijing University of Aeronautics and Astronautics,2005,31(3):270-273(in Chinese)
    [8] Fedorov A V, Khokhlov A P.Receptivity of hypersonic boundary layer to wall disturbances[J].Theoretical and Computational Fluid Dynamics,2002,15:231-254
    [9] Malik M R, Lin R S,Sengupta R.Computation of hypersonic boundary-layer response to external disturbances[R].AIAA Paper 1999-0411,1999
    [10] Maslov A A, Kudryavtsev A N,Mironov S G,et al.Numerical simulation of receptivity of a hypersonic boundary layer to acoustic disturbances[J].Journal of Applied Mechanics and Technical Physics,2007,48(3):368-374
    [11] Anatoli T, Wang X W,Zhong X L.Numerical simulation and t-heoretical analysis of perturbations in hypersonic boundary layers[J].AIAA Journal,2011,49(3):463-471
    [12] Wheaton B M, Juliano T J,Berridge D C,et al.Instability and transition measurements in the Mach-6 quiet tunnel[R].AIAA Paper 2009-3559,2009
    [13] Saric W S, Reed H L,Kerschen E J.Boundary-layer receptivity to freestream disturbances[J].Annual Review of Fluid Mechanics,2002,34:291-319
    [14] 梁贤. 高超声速钝锥边界层稳定性特征[D].上海:上海大学,2009 Liang Xian.Boundary layer stability characteristics of hypersonic flow over a blunt cone[D].Shanghai:Shanghai University,2009(in Chinese)
    [15] Kursat K, Ponnampalam B,Osama A K.Effects of nose bluntness on hypersonic boundary-layer receptivity and stability over cones[J].AIAA Journal,2011,49(12):2593-2606
    [16] Jiang G S, Shu C W.Efficient implementation of weighted ENO schemes[J].Journal of Computational Physics,1996,126: 202-228
    [17] Liu X D, Osher S,Chan T.Weighted essentially non-oscillatory schemes[J].Journal of Computational Physics,1994,115: 200-212
    [18] Lobb R K. Experimental measurement of shock detachment distance on spheres fired in air at hypervelocities[M].Washington:Defense Technical Information Center,1962
    [19] Zhang Y D, Fu D X,Ma Y W,et al.Receptivity to free-stream disturbance waves for hypersonic flow over a blunt cone[J].Science in China Series G:Physics,Mechanics & Astronomy,2008,51(11):1682-1690
    [20] Prakash A, Parsons N,Wang X,et al.High-order shock-fitting methods for direct numerical simulation of hypersonic flow with chemical and thermal nonequilibrium[J].Journal of Computational Physics,2011,230(23):8474-8507
    [21] Liang X, Li X L,Fu D X,et al.Effects of wall temperature on boundary layer stability over a blunt cone at Mach 7.99[J].Computers & Fluids,2010,39(2):359-371
    [22] Kovasznay L S G. Turbulence in supersonic flow[J].Journal of the Aeronautical Sciences,1953,20(10):657-682
    [23] Zhong X L, Ma Y B.Boundary-layer receptivity of Mach 7.99 flow over a blunt cone to free-stream acoustic waves[J].Journal of Fluid Mechanics,2006,556:55-103
    [24] Malik M R. Prediction and control of transition in supersonic and hypersonic boundary layers[J].AIAA Journal,1998, 27(11): 1487-1493
  • 加载中
计量
  • 文章访问数:  1157
  • HTML全文浏览量:  63
  • PDF下载量:  508
  • 被引次数: 0
出版历程
  • 收稿日期:  2013-06-07
  • 网络出版日期:  2014-05-20

目录

    /

    返回文章
    返回
    常见问答