Advanced Search
Volume 40 Issue 5
May  2014
Turn off MathJax
Article Contents
Journal of Beijing University of Aeronautics and Astronautics  > 2014  >  40(5): 675-684.
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)
shu

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

doi: 10.13700/j.bh.1001-5965.2013.0330

  • College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin 150001, China

  • Received Date: 07 Jun 2013
  • Publish Date: 20 May 2014
    Abstract
  • To investigate the receptivity characteristic of hypersonic flow under the action of free stream pulse wave, a high-order finite difference method was used to do numerical simulation of hypersonic unsteady flow over a blunt wedge with slow acoustic wave in free stream. The evolution of disturbance wave modes in boundary layer was analyzed by Fourier frequency spectral analysis. Results show that different frequency disturbance modes present different changes along streamline in boundary layer under freestream pulse disturbance. Disturbance waves in the boundary layer are mainly a fundamental mode. Ranging from the nose to the non-nose, the dominant mode shifts to high frequency rapidly; while in the region far from the nose, the shift to high frequency is very slow. In general, along the flow direction the low frequency component decreases quickly; the high frequency, especially the second harmonic mode component increases. Keen competition is accompanied by energy transformation exists among different modes in boundary layer. The dominant mode has an inhibitory action on the other modes.

     

    • FullText(HTML)
  • loading
    • References(24)
  • [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
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 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
    Get Citation
    PDF
    XML

    Article Metrics

    Article views(1193) PDF downloads(509) Cited by()
    Proportional views
    Related

    Copyright © Journal of Beijing University of Aeronautics and Astronautics

    Address: Editorial Department of Journal of Beijing University of Aeronautics and Astronautics, 37 Xueyuan Road, Haidian District, Beijing Post Code: 100191 Email: jbuaa@buaa.edu.cn

    Supported by: Beijing Renhe Information Technology Co., Ltd.    

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return