Flow Separation in Shock Wave Boundary Layer Interactions

1994 ◽  
Vol 116 (1) ◽  
pp. 98-103 ◽  
Author(s):  
A. Hamed ◽  
A. Kumar
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Flow Separation ◽  
Characteristic Length ◽  
Separated Flow ◽  
Surface Cooling ◽  
Flat Plates ◽  
Shock Interactions ◽  
Wave Boundary ◽  
Incipient Separation

This work presents an assessment of the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consists of selected configurations where the only characteristic length in the iteration is the incoming boundary layer thickness. It consists of two-dimensional and axisymmetric interactions in compression corners or cylinder-flares, and externally generated oblique shock interactions with boundary layers over flat plates or cylindrical surfaces. The conditions leading to flow separation and the empirical correlations for incipient separation are reviewed. The effects of Mach number, Reynolds number, surface cooling, and the methods of detecting separation are discussed.

Hypersonic Flow Separation in Shock Wave Boundary Layer Interactions

1992 ◽  
Author(s):  
A. Hamed ◽  
Ajay Kumar
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Flow Separation ◽  
Characteristic Length ◽  
Separated Flow ◽  
Surface Cooling ◽  
Flat Plates ◽  
Shock Interactions ◽  
Wave Boundary ◽  
Incipient Separation

This work presents an assessment of the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consist of selected configurations where the only characteristic length in the interation is the incoming boundary layer thickness. It consists of two dimensional and axisymmetric interactions in compression corners or cylinder-flares, and externally generated oblique shock interactions with boundary layers over flat plates or cylindrical surfaces. The conditions leading to flow separation and the empirical correlations for incipient separation are reviewed. The effects of Mach number, Reynolds number, surface cooling and the methods of detecting separation are discussed.

Experimental study of the mean structure and quasi-conical scaling of a swept-compression-ramp interaction at Mach 2

2018 ◽  
Vol 841 ◽  
pp. 1-27 ◽  
Author(s):  
Leon Vanstone ◽  
Mustafa Nail Musta ◽  
Serdar Seckin ◽  
Noel Clemens
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Particle Image Velocimetry ◽  
Flow Field ◽  
Scaling Laws ◽  
Particle Image ◽  
Separated Flow ◽  
Image Velocimetry ◽  
The Mean ◽  
Wave Boundary

This study investigates the mean flow structure of two shock-wave boundary-layer interactions generated by moderately swept compression ramps in a Mach 2 flow. The ramps have a compression angle of either $19^{\circ }$ or $22.5^{\circ }$ and a sweep angle of $30^{\circ }$. The primary diagnostic methods used for this study are surface-streakline flow visualization and particle image velocimetry. The shock-wave boundary-layer interactions are shown to be quasi-conical, with the intermittent region, separation line and reattachment line all scaling in a self-similar manner outside of the inception region. This is one of the first studies to investigate the flow field of a swept ramp using particle image velocimetry, allowing more sensitive measurements of the velocity flow field than previously possible. It is observed that the streamwise velocity component outside of the separated flow reaches the quasi-conical state at the same time as the bulk surface flow features. However, the streamwise and cross-stream components within the separated flow take longer to recover to the quasi-conical state, which indicates that the inception region for these low-magnitude velocity components is actually larger than was previously assumed. Specific scaling laws reported previously in the literature are also investigated and the results of this study are shown to scale similarly to these related interactions. Certain limiting cases of the scaling laws are explored that have potential implications for the interpretation of cylindrical and quasi-conical scaling.

scholarly journals Incipient separation in shock wave/boundary layer interactions as induced by sharp fin

Shock Waves ◽  
2006 ◽  
Vol 15 (6) ◽  
pp. 425-436
Author(s):  
Hua-Shu Dou ◽  
Boo Cheong Khoo ◽  
Khoon Seng Yeo
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Wave Boundary Layer ◽  
Wave Boundary ◽  
Incipient Separation

RANS Modelling of Shock-Wave Boundary Layer Interaction in a Mixed Compression Axisymmetric Hypersonic Intake

2016 ◽  
Vol 846 ◽  
pp. 61-66
Author(s):  
Abhijeet Kumar ◽  
Ben Thornber
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Computational Study ◽  
Oblique Shock ◽  
Bow Shock ◽  
Shock Interactions ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Wave Boundary

This work focuses on developing a design methodology for a mixed compression axisymmetric hypersonic intake and numerically computing flow around the designed intake using RANS methods to study shock/shock and shock wave/boundary layer interaction. The focus of the computational study is on the effect of increasing the blunt radius of the cowl lip on the resulting shock/shock interaction between the oblique shock emanating from the cone compression apex and the bow shock on the cowl lip; as well the resulting reflected oblique shock boundary layer interaction from the cowl tip onto the cone compression surface. Three (3) radii are tested: 2mm, 16mm and 32mm at Mach 2 and the study is extended to a nominal 16mm condition at Mach 5. It is found that with increasing cowl-lip radius the magnitude of the shock-wave/boundary layer interaction increases significantly. Separation on the cone compression surface is observed at the 16mm and 32mm case at the Mach 2 position and in the 16mm case at the Mach 5 position. In addition in the 16mm and 32mm cases at the Mach 2 position, a Mach stem is observed. The shock/shock interactions, however, are found to be less dramatic. Type III and IV phenomena are observed, however, there is limited interference with the bow shock.

Incipient Separation in Laminar Ramp-Induced Shock-Wave/Boundary-Layer Interactions

AIAA Journal ◽  
2018 ◽  
Vol 56 (2) ◽  
pp. 524-531 ◽  
Author(s):  
James R. Grisham ◽  
Brian H. Dennis ◽  
Frank K. Lu
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Wave Boundary Layer ◽  
Wave Boundary ◽  
Incipient Separation
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