The interaction of an oblique shock wave with a laminar boundary layer revisited. An experimental and numerical study

1987 ◽  
Vol 177 ◽  
pp. 247-263 ◽  
Author(s):  
G. Degrez ◽  
C. H. Boccadoro ◽  
J. F. Wendt
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Laminar Boundary Layer ◽  
Stokes Equations ◽  
Numerical Study ◽  
Pressure Ratio ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Approximate Factorization ◽  
Pressure Distributions

An investigation of an oblique shock wave/laminar boundary layer interaction is presented. The Mach number was 2.15, the Reynolds number was 105 and the overall pressure ratio was 1.55. The interation has been demonstrated to be laminar and nominally two-dimensional. Experimental results include pressure distributions on the plate and single component laser-Doppler velocimetry velocity measurements both in the attached and separated regions.The numerical results have been obtained by solving the full compressible Navier-Stokes equations with the implicit approximate factorization algorithm by Beam & Warming (1980). Comparison with experimental data shows good agreement in terms of pressure distributions, positions of separation and reattachment and velocity profiles.

Study of the Interaction of Shock Wave / Laminar Boundary Layer

2011 ◽  
Vol 274 ◽  
pp. 53-60
Author(s):  
Hamza Gouidmi ◽  
Abdelhadi Beghidja ◽  
Mohamadi Said ◽  
Razik Benderradji
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Laminar Boundary Layer ◽  
Supersonic Nozzle ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Interaction Zone ◽  
Surface Reflection ◽  
Commercial Code ◽  
Wave Induced

We are interested In this study to the interaction between oblique shock wave, induced by a surface of a supersonic nozzle with an angle of inclination of θw=8.5°, by a laminar boundary layer generated by a flat surface (reflection of oblique shock on a flat wall) . We studied also the problem of the development of the interaction zone and its unsteadiness. Our study is based on complex numerical simulation of interaction of shock wave / boundary layer and on their disturbance found within the interaction zone. This is the area of unsteady physical characteristics. This study was conducted under condition that the flow is compressible, of laminar and two-dimensional character. We treated also the point of detachment of the boundary layer by varying the value of the upstream Mach number. We compared our results (obtained by the commercial code FLUENT) with those found numerically and experimentally.

scholarly journals Instabilities in oblique shock wave/laminar boundary-layer interactions

2016 ◽  
Vol 789 ◽  
pp. 1-35 ◽  
Author(s):  
F. Guiho ◽  
F. Alizard ◽  
J.-Ch. Robinet
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Shear Layer ◽  
Laminar Boundary Layer ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Two Dimensional ◽  
Linear Framework ◽  
Displacement Thickness ◽  
The Impact

The interaction of an oblique shock wave and a laminar boundary layer developing over a flat plate is investigated by means of numerical simulation and global linear-stability analysis. Under the selected flow conditions (free-stream Mach numbers, Reynolds numbers and shock-wave angles), the incoming boundary layer undergoes separation due to the adverse pressure gradient. For a wide range of flow parameters, the oblique shock wave/boundary-layer interaction (OSWBLI) is seen to be globally stable. We show that the onset of two-dimensional large-scale structures is generated by selective noise amplification that is described for each frequency, in a linear framework, by wave-packet trains composed of several global modes. A detailed analysis of both the eigenspectrum and eigenfunctions gives some insight into the relationship between spatial scales (shape and localization) and frequencies. In particular, OSWBLI exhibits a universal behaviour. The lowest frequencies correspond to structures mainly located near the separated shock that emit radiation in the form of Mach waves and are scaled by the interaction length. The medium frequencies are associated with structures mainly localized in the shear layer and are scaled by the displacement thickness at the impact. The linear process by which OSWBLI selects frequencies is analysed by means of the global resolvent. It shows that unsteadiness are mainly associated with instabilities arising from the shear layer. For the lower frequency range, there is no particular selectivity in a linear framework. Two-dimensional numerical simulations show that the linear behaviour is modified for moderate forcing amplitudes by nonlinear mechanisms leading to a significant amplification of low frequencies. Finally, based on the present results, we draw some hypotheses concerning the onset of unsteadiness observed in shock wave/turbulent boundary-layer interactions.

Transient growth in oblique shock wave/laminar boundary layer interactions at Mach 5.92

2018 ◽  
Author(s):  
Nathaniel J. Hildebrand ◽  
Joseph W. Nichols ◽  
Graham V. Candler ◽  
Mihailo Jovanovic
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Laminar Boundary Layer ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Transient Growth

Sensitivity analysis for the control of oblique shock wave/laminar boundary layer interactions at Mach 5.92

2017 ◽  
Author(s):  
Nathaniel J. Hildebrand ◽  
Anubhav Dwivedi ◽  
Joseph W. Nichols ◽  
Graham V. Candler ◽  
Mihailo R. Jovanovic
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Sensitivity Analysis ◽  
Laminar Boundary Layer ◽  
Oblique Shock ◽  
Oblique Shock Wave
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