Experimental Investigation of the Flow Structure for Shock Wave/Boundary Layer Interactions at an Intersecting Normal and Spanwise Plane

2011 ◽  
Author(s):  
D. Burton ◽  
Holger Babinsky ◽  
Paul Bruce
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Experimental Investigation ◽  
Flow Structure ◽  
Wave Boundary Layer ◽  
Wave Boundary

Experimental investigation of dual swept shock wave/boundary layer interactions

2021 ◽  
Author(s):  
Hang Zhang ◽  
Xin Li ◽  
Huijun Tan ◽  
Shu Sun ◽  
Jinyan Wu ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Experimental Investigation ◽  
Wave Boundary Layer ◽  
Wave Boundary

Shock wave–boundary layer interactions in rectangular inlets: three-dimensional separation topology and critical points

2014 ◽  
Vol 756 ◽  
pp. 328-353 ◽  
Author(s):  
W. Ethan Eagle ◽  
James F. Driscoll
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Flow Structure ◽  
Critical Points ◽  
Saddle Points ◽  
Bottom Wall ◽  
Oblique Shock Wave ◽  
Wave Boundary Layer ◽  
Separation Zones ◽  
Wave Boundary

AbstractThe interaction between two separated flow regions was studied for the fundamental problem of a shock wave–boundary layer interaction (SBLI) within a rectangular inlet. One motivation is that the inlet of an engine on a supersonic aircraft may contain separation zones on the sidewalls and the bottom wall; if one region separates first it can alter the flow on the other wall and lead to engine unstart. In our work an oblique shock wave was generated by a wedge suspended from the upper wall of a Mach 2.75 wind tunnel. Stereo particle image velocimetry (PIV) measurements were recorded in 25 planes that include all three possible orthogonal orientations. The lateral velocity and vorticity measurements help to explain the underlying flow structure and these quantities were not measured previously for this problem. It is concluded that the sidewall and bottom wall separation zones interact due to an underlying flow structure that is similar to the two types of 3-D separation patterns previously described by Tobak & Peake (Annu. Rev. Fluid Mech., vol. 14, 1982, pp. 61–85). Separation first occurs at an upstream location where the shock interacts with the sidewall. Lateral velocities direct flow toward the centreline to cause separation on the bottom wall. This causes significant curvature of the shock wave, so that even the region near the tunnel centreline cannot be explained by conventional 2-D concepts. A number of critical points (saddle points, nodes, focus points) were identified. Results are consistent with the general ideas of Burton & Babinsky (J. Fluid Mech., vol. 707, 2012, pp. 287–306) and help to provide details of how the sidewalls redistribute the adverse pressure gradient in space.

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