Numerical study of the oscillations induced by shock/shock interaction in hypersonic double-wedge flows

Hu, Zongmin; Myong, R.S.; Wang, C.; Cho, T. H.; Jiang, Zonglin

doi:10.1007/s00193-008-0138-x

Cited by 29 publications

(8 citation statements)

References 15 publications

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“…Numerical studies on the similar problem were conducted elsewhere. 2,3,6,9,10 However, the existence of an abnormal oMR͑InMR+ InMR͒ wave configuration, to the best of our knowledge, has never been reported until the present work. Figure 2 schematically shows the MR configuration for two shock waves of opposite families.…”

mentioning

confidence: 55%

“…The detailed explanation about the wave structure can be found in a former article. 9 It is not surprising that the shock waves of opposite families, LSW2 and SW3, go on a regulation interaction at point ͑4͒ because 2 is smaller than the corresponding von Neumann criterion 2 vN . This is proven by both the shock polar analysis and the computation.…”

Section: -2 Hu Et Al Phys Fluids 21 011702 ͑2009͒mentioning

confidence: 99%

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Computational confirmation of an abnormal Mach reflection wave configuration

Wang

Zhang

et al. 2009

Physics of Fluids

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For the Mach reflection ͑MR͒ of symmetric shock waves of opposite families, only the wave configuration of an overall Mach reflection ͑oMR͒ consisting of two direct Mach reflections ͑DiMR+ DiMR͒ is theoretically admissible. For asymmetric shock waves, an oMR composed of a DiMR and an inverse Mach reflection ͑InMR͒ is possible if the two slip layers assemble a converging-diverging stream tube, while an oMR including two inverse Mach reflections ͑InMR + InMR͒ is absolutely impossible. In this paper, an overall Mach reflection configuration with double inverse MR patterns is computationally confirmed using the computational fluid dynamics technique. The aerodynamic mechanism behind such an abnormal wave pattern is illustrated. Classical two-and three-shock theories are also applied for the theoretical analysis. © 2009 American Institute of Physics. ͓DOI: 10.1063/1.3073006͔The shock wave interactions have significant impacts on the performance and reliability of a supersonic/hypersonic aircraft or a winged space shuttle during its re-entry flight. The study on shock interactions can be traced back to 1878 when Ernst Mach found two well known shock wave reflection configurations: a regular reflection ͑RR͒ and a Mach reflection ͑MR͒, which consists of a Mach stem, an incident shock, a reflected shock, and a slip layer. von Neumann 1 introduced the criteria for the RR↔ MR transition of symmetric shock waves: the von Neumann and detachment criteria. Theoretically, MR is impossible below the former, while RR is inadmissible beyond the latter. Both RR and MR are admissible between the criteria. Related research can still be found in the recent literature. [2][3][4][5][6] In the present work, an abnormal MR configuration of asymmetric shock waves is computationally confirmed over a double-wedge geometry ͑Fig.

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confidence: 55%

Section: -2 Hu Et Al Phys Fluids 21 011702 ͑2009͒mentioning

confidence: 99%

Computational confirmation of an abnormal Mach reflection wave configuration

Wang

Zhang

et al. 2009

Physics of Fluids

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“…2. It should be noted that although the wave structures look similar with those given in the previous work, 22,24 one of the differences is that the whole solution domain instead of the dual-solution domain is of interest in the present study. The flow features the interaction between shock waves of opposite families, SW3 and LSW2.…”

Section: Theoretical Analysismentioning

confidence: 66%

“…It was found that hysteresis and self-induced oscillations in the shock flow pattern can result in extremely high and unsteady loads on the wedge surfaces. 21,27 Thermally nonequilibrium effects on the transition and the oscillation were reported by Hu et al 22 where the thermal properties of the components of air are temperature dependent. Advanced RR→ MR transition due to downstream influence has been first reported in a theoretical dual-solution regime.…”

Section: Introductionmentioning

confidence: 92%

“…[12][13][14][15][16][17][18] The research on shock wave interactions is still active in recent times. 1,[19][20][21][22][23][24] The shock wave interactions have significant impacts on the performance and reliability of a high-speed aircraft. An example is the shock/shock interaction on double-wedge-like geometries in a hypersonic flow which is considered to be a fundamental research problem related to hypersonic flights.…”

Section: Introductionmentioning

confidence: 99%

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Geometric criterion for RR↔MR transition in hypersonic double-wedge flows

Hu¹,

Gao²,

Myong³

et al. 2010

Physics of Fluids

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In a previous research article ͓Z. M. Hu et al., Phys. Fluids 21, 011701 ͑2009͔͒, an overall Mach reflection ͑oMR͒ configuration with double inverse Mach reflection patterns was computationally confirmed when a double-wedge geometry interacts with a hypersonic flow. Extended computations are conducted in this paper and compared to analytical solutions based on the classical two-and three-shock theories. A geometric criterion is proposed for the transition between regular reflection and Mach reflection occurring inside the parameter space where a type V interaction of shock wave presents in hypersonic double-wedge flows. An oMR solution is allowed by the geometric criterion, while it is theoretically inadmissible. In the vicinity of symmetric condition, regular to Mach reflection transition can also be triggered prior to the theoretical criterion by disturbance generated by a slight increase in the second wedge angle.

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