Investigation of Unsteady Edney Type IV and VII Shock–Shock Interactions

Windisch, Christian; Reinartz, Birgit; Müller, Siegfried

doi:10.2514/1.j054298

Cited by 24 publications

(12 citation statements)

References 28 publications

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“…A number of studies have been conducted to study the flow pattern (cf. Frame & Lewis 1997; Windisch, Reinartz & Müller 2016), transition between various flow patterns (cf. Bramlette 1974), heat load (cf.…”

Section: Introductionmentioning

confidence: 99%

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Type IV shock interaction with a two-branch structured transonic jet

Bai

2022

J. Fluid Mech.

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Type IV shock interference has two triple points which produce two sliplines, forming a narrow jet that penetrates into the subsonic flow region behind the bow shock. Type IV shock interference in the case that the jet is supersonic has been extensively studied in the past. In this paper, type IV shock interference where the jet is transonic is studied. The transition condition from a supersonic to a transonic jet is identified and the influence of compression Mach waves, created inside the leading portion of the jet due to the pressure gradient outside the jet, on the transition and jet shape is analysed. It is found that these compression waves advance the transition from a supersonic to a transonic jet and make the flow inside the transonic jet have a two-branch structure: the lower branch is subsonic, the upper branch is supersonic and is composed of a combination of compressive and expansive waves. The mechanism by which the two-branch structure is produced is explained.

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Section: Introductionmentioning

confidence: 99%

“…1988; Gaitonde & Shang 1995; Chu & Lu 2012; Windisch et al. 2016; Khatt & Jagadeesh 2018). See the review of Grasso et al.…”

Section: Introductionmentioning

confidence: 99%

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Type IV shock interaction with a two-branch structured transonic jet

Bai

2022

J. Fluid Mech.

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“…Despite the extensive work done on CO 2 hypersonic flows and its nonequilibrium physics, the literature discussing shock interaction patterns for this gas mixture is scarce to the best of the authors' knowledge. Windisch et al [13] simulated the impingement of an oblique shock on a bow shock in front of a cylinder in a CO2-dominated flow, from which a type VII interaction pattern was obtained. A comparison with the same test-case but considering instead an N 2 mixture revealed that the post-shock temperatures were significantly lower for the gas model of the Martian atmosphere, resulting in a higher fluid density and a much smaller shock stand-off distance.…”

Section: Introductionmentioning

confidence: 99%

Influence of Thermochemical Modelling of CO2-N2 Mixtures on the Shock Interaction Patterns at Hypersonic Regimes

Garbacz

Morgado

Fossati³

et al. 2021

Aiaa Aviation 2021 Forum

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The effect of finite-rate internal energy transfer on shock interaction mechanisms of CO 2dominated flows is investigated. The polyatomic molecule has a relatively low characteristic vibrational temperature that causes vibrational degrees of freedom to be excited across a shock wave at hypersonic regimes. In this paper, the impact of accounting for the time associated to the relaxation of this process, as opposed to assuming instant thermal equilibrium, on the shock structures occurring in the flowfield over a double-wedge geometry is numerically studied. A Mach 9 flow over two different geometries is simulated with two different models, the two-temperature model of Park and the thermally perfect gas model. Simulations are carried out with the SU2 software that is coupled to the Mutation++ library, providing thermodynamic, chemical kinetic and transport properties of any mixture of gases for a given state of the flow. Anisotropic mesh adaption is used with the AMG library to accurately capture highly directional and high-gradient localized flow features. Results show that different ways of modelling the effect of vibrational relaxation have a major impact on the size of the compression corner separation bubble, leading to different shock wave systems in this region. As a consequence, the obtained shock interaction mechanisms differ as well. The shock patterns obtained for the thermally perfect gas model result in stronger impingement on the surface and higher aerodynamic loads of pressure and heat flux.

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“…To the best of the authors' knowledge, the literature discussing the identification of shock wave interference patterns and the associated aerothermal loads in the case of CO 2dominated flows is still not fully consolidated. Windisch et al [19] simulated the intersection between an oblique shock and a bow shock in front of a cylinder with a CO 2dominated flow and observed the type VII interaction. A comparison with the same test case but considering instead a N 2 mixture revealed that the post-shock temperatures were significantly lower for the gas model of the Martian atmosphere, resulting in a higher fluid density and a much smaller shock stand-off distance.…”

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confidence: 99%

Shock interactions in inviscid air and $$\hbox {CO}_2$$–$$\hbox {N}_2$$ flows in thermochemical non-equilibrium

et al. 2021

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The present study aims at providing insights into shock wave interference patterns in gas flows when a mixture different than air is considered. High-energy non-equilibrium flows of air and $$\hbox {CO}_2$$ CO 2 –$$\hbox {N}_2$$ N 2 over a double-wedge geometry are studied numerically. The impact of freestream temperature on the non-equilibrium shock interaction patterns is investigated by simulating two different sets of freestream conditions. To this purpose, the SU2 solver has been extended to account for the conservation of chemical species as well as multiple energies and coupled to the Mutation++ library (Multicomponent Thermodynamic And Transport properties for IONized gases in C++) that provides all the necessary thermochemical properties of the mixture and chemical species. An analysis of the shock interference patterns is presented with respect to the existing taxonomy of interactions. A comparison between calorically perfect ideal gas and non-equilibrium simulations confirms that non-equilibrium effects greatly influence the shock interaction patterns. When thermochemical relaxation is considered, a type VI interaction is obtained for the $$\hbox {CO}_2$$ CO 2 -dominated flow, for both freestream temperatures of 300 K and 1000 K; for air, a type V six-shock interaction and a type VI interaction are obtained, respectively. We conclude that the increase in freestream temperature has a large impact on the shock interaction pattern of the air flow, whereas for the $$\hbox {CO}_2$$ CO 2 –$$\hbox {N}_2$$ N 2 flow the pattern does not change.

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Investigation of Unsteady Edney Type IV and VII Shock–Shock Interactions

Cited by 24 publications

References 28 publications

Type IV shock interaction with a two-branch structured transonic jet

Type IV shock interaction with a two-branch structured transonic jet

Influence of Thermochemical Modelling of CO2-N2 Mixtures on the Shock Interaction Patterns at Hypersonic Regimes

Shock interactions in inviscid air and $$\hbox {CO}_2$$–$$\hbox {N}_2$$ flows in thermochemical non-equilibrium

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