Author(s): LIU Kai-ping, LUO Ji-sheng, Department of Mechanics, School of Mechanical Engineering, Tianjin University
Pages: 168-178
Year: 2016 Issue:  1
Journal: Journal of Aerospace Power
Keyword:  transition prediction; boundary layer; local disturbance; concave groove; flow stability; eN method;
Abstract: In order to predict the transition position using e N method for flat boundary layer with concave groove,the effects of concave groove on the evolution of disturbance in supersonic boundary layer with Mach number of 4.5were studied by numerical simulation and flow stability method.The amplitude and growth rate distribution along the flow direction with two sizes of concave groove was revealed.The results show that the range of effect of concave groove on the basic flow is only limited in the concave groove and near range.Concave groove has a suppressed effect on the evolution of disturbance to some extent,the bigger size means the more obvious inhibitory effect.After concave groove,the effect of concave groove on the growth rate of disturbance amplitude is little,and relative variation is smaller than 2%.At the same time,the position of transition can be predicted more accurately with a smaller concave groove by e Nmethod combined with stability analysis and a correction factor of N.