MENG Xiang-nan, WANG Zhen-qing, TANG Xiao-jun, Lü Hong-qing. Numerical Simulation and Impact Studies of Hypersonic Unsteady Flow Under the Action of Pulse Disturbance Wave[J]. Applied Mathematics and Mechanics, 2013, 34(2): 127-138. doi: 10.3879/j.issn.1000-0887.2013.02.003
Citation: MENG Xiang-nan, WANG Zhen-qing, TANG Xiao-jun, Lü Hong-qing. Numerical Simulation and Impact Studies of Hypersonic Unsteady Flow Under the Action of Pulse Disturbance Wave[J]. Applied Mathematics and Mechanics, 2013, 34(2): 127-138. doi: 10.3879/j.issn.1000-0887.2013.02.003

Numerical Simulation and Impact Studies of Hypersonic Unsteady Flow Under the Action of Pulse Disturbance Wave

doi: 10.3879/j.issn.1000-0887.2013.02.003
  • Received Date: 2012-12-31
  • Rev Recd Date: 2013-01-07
  • Publish Date: 2013-02-15
  • Direct numerical simulation of pulse disturbance in hypersonic flow over a blunt cone by using high-order accuracy finite difference method was performed. The interaction between fast acoustic wave and hypersonic flow field was studied; the evolution and development process of disturbance wave in the boundary layer was analyzed by Fourier frequency spectral analysis (FFSA). Results show that the disturbance into the flow field interacted with the shock wave and boundary layer, which makes bow shock bent obviously and disturbance enlarged, with obvious demarcations between the disturbance near the wall and in the outer boundary layer. The perturbation amplitudes on the nose are much larger than on the other locations. At the stage of the development of disturbance in the boundary layer, some perturbation modes continue to grow, some are filtered and seldom grow, even decay, and also some decay firstly and then grow. In general, the low frequency perturbation modes are dominated within a nose radius, with the disturbance development from upstream to downstream, the high frequency components increase quickly and low frequency components almost are restrained to grow.
  • loading
  • [1]
    Fujita M.Axisymmetric oscillations of an opposing jet from a hemispherical nose[J]. AIAA Journal,1995, 33(10):1850-1856.
    [2]
    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.
    [3]
    Venukumar B, Jagadeesh G, Reddy K P J.Counter flow drag reduction by supersonic jet for a blunt body in hypersonic flow[J]. Physics of Fluids,2006, 18(11): 571-576.
    [4]
    Hayashi K, Aso S, Tani Y.Experimental study on thermal protection system by opposing jet in supersonic flow[J]. Journal of Spacecraft and Rockets,2006, 43(1): 233-235.
    [5]
    童中翔, 董小龙.外挂对载机气动特性的影响研究[J].飞行力学, 2005, 23(2): 32-35.(TONG Zhong-xiang, DONG Xiao-long.Study on influence of external stores on aerodynamic characteristics of the fighter plane[J]. Flight Dynamics,2005, 23(2): 32-35.(in Chinese))
    [6]
    Yurkovich R N.Status of unsteady aerodynamic prediction for flutter of highperformance aircraft[J]. Journal of Aircraft,2003, 40(5): 832-842.
    [7]
    Li X L, Fu D X, Ma Y W.Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack [J]. Physics of Fluids,2010, 22(2):1-18.
    [8]
    ZHOU Y, Li X L, Fu D X, Ma Y W.Coherent structures in transition of a flatplate boundary layer at Ma=0.7[J]. Chinese Physics Letters,2007,24(1):147-150.
    [9]
    Zhang Y D, Fu D X, Ma Y W, Li X L.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.
    [10]
    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 Zhong-shu, WEN Gong-bi.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))
    [11]
    滕宏辉, 姜宗林.一维过驱动爆轰波形成的数值研究[J].计算物理, 2008, 25(1): 5864.(TENG Hong-hui, JIANG Zong-lin.Numerical investigation of onedimensional overdriven detonation initiation[J]. Chinese Journal of Computational Physics,2008, 25(1): 58-64.(in Chinese))
    [12]
    Li X L, Fu D X, Ma Y W.Direct numerical simulation of compressible isotropic turbulence[J]. Science in China, Series A,2002, 45(11): 1452-1460.
    [13]
    Bonorchis D, Nurick G N.The analysis and simulation of welded stiffener plates subjected to localized blast loading [J]. International Journal of Impact Engineering,2010, 37: 260-273.
    [14]
    杨云军, 沈清, 詹慧玲, 周伟江.高超声速小钝锥边界层非对称转捩研究[J].宇航学报, 2008, 29(1): 34-39.(YANG Yun-jun, SHEN Qing, ZHAN Hui-ling, ZHOU Wei-jiang.Investigation on asymmetric transition about hypersonic boundary layer over a slight blunt cone[J]. Journal of Astronautics,2008, 29(1): 34-39.(in Chinese))
    [15]
    Pettersson Reif B A, Durbin P A, Ooi A.Modeling rotational effects in eddyviscosity closures[J]. International Journal of Heat and Fluid Flow, 1999, 20(6): 563-573.
    [16]
    傅德薰.计算空气动力学[M].北京:宇航出版社,1994.(FU De-xun. Computational Aerodynamics [M].Beijing: Aerospace Press, 1994.(in Chinese))
    [17]
    Liu X D, Osher S, Chan T.Weighted essentially nonoscillatory schemes[J]. Journal of Computational Physics,1994, 115:200-212.
    [18]
    Zhong X L, Ma Y H.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.
    [19]
    Kovasznay L S G.Turbulence in supersonic flow[J]. J Aero Sci, 1953, 20: 657-682.
    [20]
    Liang X, Li X L, Fu D X, Ma Y W.Effects of wall temperature on boundary layer stability over a blunt cone at Mach 7.99[J]. Computers & Fluids,2010, 39(2): 359-371.
  • 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 (1764) PDF downloads(1067) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return