Domains and Boundaries of Pseudo-Stationary Oblique Shock-Wave Reflections.

A direct comparison is made for several occurrences of oblique shock-wave reflections between interferometric results obtained at the University of Toronto Institute for Aerospace Studies (UTIAS) 10 cm x 18 cm hyper-velocity shock tube and numerical results obtained by using a current computational method for solving the Euler equations. Very good qualitative agreement is obtained for equilibrium and frozen flow fields except in small regions where the experiments were dominated by viscous flow. The quantitative agreement is very close in some cases but can be out by 10–15% in cases with non-equilibrium flow or viscous structures or both. Additional parametrized sequences of calculations are presented to assess the utility of the present numerical method in constructing the various reflection–transition lines for perfect inviscid flows in the shock-wave Mach number, wedge-angle ( M s , θ w )-plane, and the validity of the ‘boundary-layer defect’ theory.

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Nonstationary Oblique Shock-Wave Reflections: Actual Isopycnics and Numerical Experiments

AIAA Journal ◽

10.2514/3.61021 ◽

1978 ◽

Vol 16 (11) ◽

pp. 1146-1153 ◽

Cited By ~ 33

Author(s):

G. Ben-Dor ◽

I. I. Glass

Keyword(s):

Shock Wave ◽

Numerical Experiments ◽

Oblique Shock ◽

Oblique Shock Wave ◽

Wave Reflections

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Oblique Shock Wave Reflections in SF6: A Comparison of Calculation and Experiment

Dynamics of Explosions ◽

10.2514/5.9781600865800.0359.0387 ◽

1986 ◽

pp. 359-387

Keyword(s):

Shock Wave ◽

Oblique Shock ◽

Oblique Shock Wave ◽

Wave Reflections

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A parametric study of laminar and transitional oblique shock wave reflections

Journal of Fluid Mechanics ◽

10.1017/jfm.2018.165 ◽

2018 ◽

Vol 844 ◽

pp. 187-215 ◽

Cited By ~ 6

Author(s):

R. H. M. Giepman ◽

F. F. J. Schrijer ◽

B. W. van Oudheusden

Keyword(s):

Boundary Layer ◽

Shock Wave ◽

Separation Bubble ◽

Reynolds Numbers ◽

Oblique Shock ◽

Oblique Shock Wave ◽

Strong Interactions ◽

Wave Reflections ◽

Upstream Direction ◽

Free Interaction

High-resolution particle image velocimetry measurements were performed on laminar and transitional oblique shock wave reflections for a range of Mach numbers ($M=1.6{-}2.3$), Reynolds numbers ($Re_{x_{sh}}=1.4\times 10^{6}{-}3.5\times 10^{6}$) and flow deflection angles ($\unicode[STIX]{x1D703}=1^{\circ }{-}5^{\circ }$ or $p_{3}/p_{1}=1.11{-}1.64$). The laminar interactions revealed a long, flat and triangular shaped separation bubble. For relatively strong interactions ($p_{3}/p_{1}>1.2$), the bubble grows linearly in the upstream direction with increasing shock strength. Under these conditions, the boundary layer keeps an on average laminar velocity profile up to the shock impingement location, followed by a quick transition and subsequent reattachment of the boundary layer. For weaker interactions ($p_{3}/p_{1}<1.2$), the boundary layer is able to remain laminar further downstream of the bubble, which consequently results in a later reattachment of the boundary layer. The pressure distribution at the interaction onset for all laminar cases shows excellent agreement with the free-interaction theory, therefore supporting its validity even for incipiently separated laminar oblique shock wave reflections.

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