Effect of disturbances at inlet on hypersonic boundary layer transition on a blu

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Effect of disturbances at inlet on hypersonic boundary layer transition on a blunt cone at small angle of attack

To investigate the effect of different disturbances in the upstream, we present numerical simulation of transition for a hypersonic boundary layer on a 5-degree half-angle blunt cone in a freestream with Mach number 6 at 1-degree angle of attack. Evolution of small disturbances is simulated to compare with the linear stability theory (LST), indicating that LST can provide a good prediction on the growth rate of the disturbance. The effect of different disturbances on transition is investigated. Transition onset distributions along the azimuthal direction are obtained with two groups of disturbances of different frequencies. It shows that transition onset is relevant to frequencies and amplitudes of the disturbances at the inlet, and is decided by the amplitudes of most unstable waves at the inlet. According to the characteristics of environmental disturbances in most wind tunnels, we explain why transition occurs leeside-forward and windside-aft over a circular cone at an angle of attack. Moreover, the indentation phenomenon in the transition curve on the leeward is also revealed.水利论文^mf+?8S9{ t/n

作 者: Jian-xin LIU Ji-sheng LUO  
作者单位:Department of Mechanics,Tianjin University,Tianjin 300072,P.R.China 
刊 名:应用数学和力学(英文版)  EI SCI
英文刊名:APPLIED MATHEMATICS AND MECHANICS 
年,卷(期):2010 31(5) 
分类号:O354.4 O357.41 
关键词:transition   blunt cone   hypersonic  
机标关键词:angle of attacksmalldifferenthypersonic boundary layernumerical simulationtransition curvestability theorywind tunnelsMach numbergrowth ratedirectionLSTtwo 
基金项目:Project supported by the National Natural Science Foundation of China,the National Natural Science Foundation of China for Distinguished Young Scholars,the Specialized Research Fund for the Doctoral Program of Higher Education 
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