Hybrid upwind methods for the simulation of unsteady shock-wave diffraction over a cylinder

Żółtak, J.; Drikakis, Dimitris

doi:10.1016/s0045-7825(97)00342-3

Cited by 67 publications

(20 citation statements)

References 17 publications

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“…ii) the Roe's scheme (Roe 1981;Roe and Pike 1984), and iii) the hybrid Godunov-type method (labelled CBM-FVS) (Zó ltak and Drikakis 1998); the latter is a combination of the characteristic-based method (CBM) of (Eberle 1987) and the modified (Zó ltak and Drikakis 1998; Drikakis and Tsangaris 1993) Steger-Warming flux vector splitting scheme (FVS) (Steger and Warming 1981). The above Godunov-type methods have been implemented in conjunction with the MUSCL scheme (Thomas et al 1985;van Leer 1979) and an implicit unfactored solver (Zó ltak and Drikakis 1998;Drikakis and Durst 1994). Figure 2 shows the shock-bubble interaction at selected time instants as predicted by the three Godunov-type methods.…”

Section: Resultsmentioning

confidence: 99%

Mach number effects on shock-bubble interaction

2001

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An investigation of Mach number effects on the interaction of a shock wave with a cylindrical bubble, is presented. We have conducted simulations with the Euler equations for various incident shock Mach numbers (MS) in the range of 1.22 ≤ MS ≤ 6, using high-resolution Godunov-type methods and an implicit solver. Our results are found in a very good agreement with previous investigations and further reveal additional gasdynamic features with increasing the Mach number. At higher Mach numbers larger deformations of the bubble occur and a secondary-reflected shock wave arises upstream of the bubble. Negative vorticity forms at all Mach numbers, but the "c-shaped" vortical structure appeared at MS = 1.22 gives its place to a circular-shaped structure at higher Mach numbers. The computations reveal that the (instantaneous) displacements of the upstream, downstream and jet interfaces are not significantly affected by the incident Mach number for values (approximately) greater than MS = 2.5. With increasing the incident Mach number, the speed of the jet (arising from the centre of the bubble during the interaction) also increases.

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Section: Resultsmentioning

confidence: 99%

Mach number effects on shock-bubble interaction

2001

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“…26-28͒ has been employed, which has been previously applied to a wide range of flows featuring shock waves and turbulence. 26,[29][30][31][32][33][34][35][36] The remainder of this paper is organized as follows. Sections II and III present the governing equations and numerical methods employed in this study.…”

Section: Introductionmentioning

confidence: 99%

Richtmyer–Meshkov turbulent mixing arising from an inclined material interface with realistic surface perturbations and reshocked flow

et al. 2011

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This paper presents a numerical study of turbulent mixing due to the interaction of a shock wave with an inclined material interface. The interface between the two gases is modeled by geometrical random multimode perturbations represented by different surface perturbation power spectra with the same standard deviation. Simulations of the Richtmyer-Meshkov instability and associated turbulent mixing have been performed using high-resolution implicit large eddy simulations. Qualitative comparisons with experimental flow visualizations are presented. The key integral properties have been examined for different interface perturbations. It is shown that turbulent mixing is reduced when the initial perturbations are concentrated at short wavelengths. The form of the initial perturbation has strong effects on the development of small-scale flow structures, but this effect is diminished at late times.

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“…There are different strategies and theories that could be used for this purpose. For example, the method of Drikakis and Tsangaris had applied a second‐order artificial dissipation to improve the performance of basis FVS schemes. This simple and effective strategy could be also used to improve the numerical stability of SLAU scheme.…”

Section: Hybrid Schemementioning

confidence: 99%

“…In fact, it was proved to be straightforward and practical to develop a hybrid upwind scheme for improving both the accuracy and stability of numerical computations. Drikakis and Tsangaris designed a generalized hybrid flux‐vector‐splitting (FVS) scheme by adding a second‐order artificial dissipation in the regions of strong shock waves. The scheme was validated by a serial of Euler and Navier–Stokes cases.…”

Section: Introductionmentioning

confidence: 99%

A robust low‐dissipation AUSM‐family scheme for numerical shock stability on unstructured grids

Zhang

Chen

et al. 2016

Numerical Methods in Fluids

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Summary The simple low‐dissipation advection upwind splitting method (SLAU) scheme is a parameter‐free, low‐dissipation upwind scheme that has been applied in a wide range of aerodynamic numerical simulations. In spite of its successful applications, the SLAU scheme could be showing shock instabilities on unstructured grids, as many other contact resolved upwind schemes. Therefore, a hybrid upwind flux scheme is devised for improving the shock stability of SLAU scheme, without compromising on accuracy and low Mach number performance. Numerical flux function of the hybrid scheme is written in a general form, in which only the scalar dissipation term is different from that of the SLAU scheme. The hybrid dissipation term is defined by using a differentiable multidimensional‐shock‐detection pressure weight function, and the dissipation term of SLAU scheme is combined with that of the Van Leer scheme. Furthermore, the hybrid dissipation term is only applied for the solution of momentum fluxes in numerical flux function. Based on the numerical test results, the hybrid scheme is deemed to be a successful improvement on the shock stability of SLAU scheme, without compromising on the efficiency and accuracy. Copyright © 2016 John Wiley & Sons, Ltd.

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Hybrid upwind methods for the simulation of unsteady shock-wave diffraction over a cylinder

Cited by 67 publications

References 17 publications

Mach number effects on shock-bubble interaction

Mach number effects on shock-bubble interaction

Richtmyer–Meshkov turbulent mixing arising from an inclined material interface with realistic surface perturbations and reshocked flow

A robust low‐dissipation AUSM‐family scheme for numerical shock stability on unstructured grids

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