The Research of Laminar-Turbulent Transition in Hypersonic Three-Dimensional Boundary Layer  

作　　者：Marat A.GOLDFELD Evgeniy V.ORLIK 

机构地区：[1]Institute of Theoretical and Applied Mechanics 4/1 Institutskaya Str.,Novosibirsk 630090,Russia,Institute of Theoretical and Applied Mechanics 4/1 Institutskaya Str.,Novosibirsk 630090,Russia

出　　处：《Journal of Thermal Science》2005年第2期103-107,共5页热科学学报（英文版）

摘　　要：The results of experimental investigation of laminar-turbulent transition in three-dimensional flow under the high continuous pressure gradient including the flow with local boundary layer separation are presented. The experimental studies were performed within the Mach number range from 4 to 6 and Reynolds number 10-60×106 1/m, the angles of attack were 0° and 5°. The experiments were carried out on the three-dimensional convergent inlet model with and without sidewalls. The influence of artificial tubulator of boundary layer on transition and flow structure was studied. The conducted researches have shown that adverse pressure gradient increase hastens transition and leads to decrease of transition area length. If pressure gradient rises velocity profile fullness increases and profile transformation from laminar to turbulent occurs. As a result of it the decrease of separation area length occurs. The same effect was reached with Reynolds number increase. These results are compared with the data on two-dimensional model with longitudinal curvature.

关 键 词：hypersonic boundary layer TRANSITION convergent inlet adverse pressure gradient. 

分 类 号：O354.3[理学—流体力学]