Wind-Tunnel Setup for Investigations of Normal Shock Wave/Boundary Layer Interaction Control

AIAA Journal ◽  
2006 ◽  
Vol 44 (11) ◽  
pp. 2803-2805 ◽  
Author(s):  
H. Ogawa ◽  
H. Babinsky
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Wind Tunnel ◽  
Normal Shock ◽  
Normal Shock Wave ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Interaction Control ◽  
Boundary Layer Interaction ◽  
Wave Boundary

Three-Dimensional Normal Shock-Wave/Boundary-Layer Interaction in a Diffuser

2013 ◽  
Vol 135 (4) ◽  
Author(s):  
Daisuke Ono ◽  
Taro Handa ◽  
Mitsuharu Masuda
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Stokes Equations ◽  
Normal Shock ◽  
3D Flow ◽  
Normal Shock Wave ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Wave Boundary

The 3D flow structure induced by a normal shock-wave/boundary-layer interaction in a transonic diffuser is experimentally and computationally investigated. In the diffuser, the shock wave is located in the diverging section. The experiments are done with wall pressure measurements, oil-flow surface visualization, and Mach number measurements with a laser-induced fluorescence (LIF) method. In the computational work, the Reynolds-averaged Navier–Stokes equations are numerically solved with the k-ω two-equation turbulence model. The numerical solution agrees reasonably well with the experiment and clarifies the vortex structure in the interaction zone along with the 3D behavior of the boundary layer downstream of the shock wave. A careful investigation of the calculated flow reveals that the vortices are generated at the foot of the shock wave. It is also found that a complicated wave configuration is formed near the diffuser corner. A flow model is constructed by considering this wave configuration. This model explains the 3D flow characteristics in the transonic diffuser very well.

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