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

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 similar to 60 X 10(6) l/m, the angles of attack were 0(0) and 5(0). The experiments were carded out on the three-dimensional convergent inlet model with and without sidewalls. The influence of artificial turbulator 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.