Experimental Study of an Incident Shock Wave/Turbulent Boundary Layer Interaction Using PIV

2006 ◽  
Author(s):  
Raymond Humble ◽  
Fulvio Scarano ◽  
Bas van Oudheusden
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Experimental Study ◽  
Turbulent Boundary Layer ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Layer Interaction ◽  
Boundary Layer Interaction

scholarly journals Unsteady aspects of an incident shock wave/turbulent boundary layer interaction

2009 ◽  
Vol 635 ◽  
pp. 47-74 ◽  
Author(s):  
R. A. HUMBLE ◽  
F. SCARANO ◽  
B. W. van OUDHEUSDEN
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Turbulent Boundary Layer ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Reflected Shock Wave ◽  
Reversed Flow ◽  
Layer Interaction ◽  
Reflected Shock ◽  
Boundary Layer Interaction

An incident shock wave/turbulent boundary layer interaction at Mach 2.1 is investigated using particle image velocimetry in combination with data processing using the proper orthogonal decomposition, to obtain an instantaneous and statistical description of the unsteady flow organization. The global structure of the interaction is observed to vary considerably in time. Although reversed flow is often measured instantaneously, on average no reversed flow is observed. On an instantaneous basis, the interaction exhibits a multi-layered structure, characterized by a relatively high-velocity outer region and low-velocity inner region. Discrete vortical structures are prevalent along their interface, which create an intermittent fluid exchange as they propagate downstream. A statistical analysis suggests that the instantaneous fullness of the incoming boundary layer velocity profile is (weakly) correlated with the size of the separation bubble and position of the reflected shock wave. The eigenmodes show an energetic association between velocity fluctuations within the incoming boundary layer, separated flow region and across the reflected shock wave, and portray subspace features that represent the phenomenology observed within the instantaneous realizations.

scholarly journals A Study on the Separation Length of Shock Wave/Turbulent Boundary Layer Interaction

2019 ◽  
Vol 2019 ◽  
pp. 1-10 ◽  
Author(s):  
Yong-yi Zhou ◽  
Yi-long Zhao ◽  
Yu-xin Zhao
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Turbulent Boundary Layer ◽  
Incident Shock ◽  
Computational Domain ◽  
Layer Interaction ◽  
Flow Parameters ◽  
Boundary Layer Interaction ◽  
High Mach ◽  
Wave Boundary

The separation length of shock wave/boundary layer interaction (SWBLI) was studied by a numerical method, which was validated by experimental results. The computational domain was two-dimensional (2-D). The flow field was an incident oblique shock interacting with a turbulent boundary layer on a flat adiabatic plate. According to the simulation data, the dependency of the separation length on the relevant flow parameters, such as the incident shock strength, Reynolds number, and Mach number, was analyzed in the range of 2≤M≤7. Based on the relations with the flow parameters, two models of the separation length at low and high Mach numbers were proposed, respectively, which can be used to predict the extent of the separation in the SWBLI.

Visualization of hypersonic incident shock wave boundary layer interaction

2020 ◽  
Vol 23 (2) ◽  
pp. 207-214 ◽  
Author(s):  
Zhang Qinghu ◽  
Zhu Zhiwei ◽  
Lin Jingzhou ◽  
Xie Futian ◽  
Zhong Jun
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Wave Boundary

Skin Friction Extracted from Surface Pressure in Incident Shock-Wave/Boundary-Layer Interaction

AIAA Journal ◽  
2021 ◽  
pp. 1-13
Author(s):  
Tianshu Liu ◽  
David M. Salazar ◽  
Jim Crafton ◽  
Nickolay Rogoshchenkov ◽  
Colleen Ryan ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Skin Friction ◽  
Surface Pressure ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Wave Boundary

Experimental Study of Shock Wave / Turbulent Boundary Layer Interaction

2010 ◽  
Vol 3 (2) ◽  
Author(s):  
Pavel Polivanov ◽  
Sidorenko Andrey ◽  
Maslov Anatoliy
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Experimental Study ◽  
Turbulent Boundary Layer ◽  
Separated Flow ◽  
Reflected Shock Wave ◽  
Oblique Shock Wave ◽  
Layer Interaction ◽  
Reflected Shock ◽  
Boundary Layer Interaction

Experimental study of separated flow in a zone of oblique shock wave / turbulent boundary layer interaction was carried out for Mach number 2 and Reynolds number Reθ = 2,7÷3,5 × 103. Streamwise pressure distribution on the model surface was obtained, Schlieren and oil-flow visualizations were performed. The paper gives detailed data of hot-wire anemometry measurements in upstream boundary layer, interaction and recovery regions. Unsteady nature of separated zone and reflected shock wave was discovered. The effect of side walls on quasi 2D structure of separated flow is described.

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