Performance of all-speed AUSM-family schemes for DNS of low Mach number turbulent channel flow

Matsuyama, Shingo

doi:10.1016/j.compfluid.2013.12.010

Cited by 25 publications

(14 citation statements)

References 32 publications

(16 reference statements)

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“…In some instances, many user-specified parameters (such as "cutoff Mach number" [32,36]) are required when designing all-speed Riemann solvers. A great deal of attention must be paid to the choice of this cutoff Mach number, otherwise the solution can be troublesome [32,55,56]. The dissipation term of the SLAU2 Riemann solver for gasdynamics, however, was designed to be automatically scaled to O(M 2 ) at low speeds, and hence, needs no expert care by the user.…”

Section: Introductionmentioning

confidence: 99%

Hybridized SLAU2–HLLI and hybridized AUSMPW$$+$$–HLLI Riemann solvers for accurate, robust, and efficient magnetohydrodynamics (MHD) simulations, part I: one-dimensional MHD

Kitamura

Balsara

2018

Shock Waves

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SLAU2 and AUSMPW+, both categorized as AUSM-type Riemann solvers, have been extensively developed in gasdynamics. They are based on a splitting of the numerical flux into advected and pressure parts. In this paper, these two Riemann solvers have been extended to magnetohydrodynamics (MHD). The SLAU2 Riemann solver has the favorable attribute that its dissipation for low-speed flows scales as O(M 2), where M is the Mach number. This is the physical scaling required for low-speed flows, and the dissipation in SLAU2 for MHD is engineered to have this low Mach number scaling. The AUSMPW+, when its pressure flux is replaced with that of SLAU2, has the same low Mach number scaling. At higher Mach numbers, however, the pressure-split Riemann solvers were found not to

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Section: Introductionmentioning

confidence: 99%

Hybridized SLAU2–HLLI and hybridized AUSMPW$$+$$–HLLI Riemann solvers for accurate, robust, and efficient magnetohydrodynamics (MHD) simulations, part I: one-dimensional MHD

Kitamura

Balsara

2018

Shock Waves

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“…There is a wealth of different approaches aiming to improve the dissipation characteristics of numerical methods for compressible flow equations, either by enabling their deployment for very low Mach number flows, or improving their resolution at low Mach number regions [32][33][34][35][36][37][38][39][40][41][42]. In the novel approach of Rieper [41,42 ], it was shown through an one-dimensional analysis that the right amount of artificial viscosity on each individual characteristic variable is a prerequisite for an upwind scheme to approximate low Mach number flows correctly.…”

Section: Introductionmentioning

confidence: 99%

Low-Mach number treatment for Finite-Volume schemes on unstructured meshes

Simmonds

Tsoutsanis

Antoniadis

et al. 2018

Applied Mathematics and Computation

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The paper presents a low-Mach number (LM) treatment technique for high-order, Finite-Volume (FV) schemes for the Euler and the compressible Navier-Stokes equations. We concentrate our efforts on the implementation of the LM treatment for the unstructured mesh framework, both in two and three spatial dimensions, and highlight the key differences compared with the method for structured grids. The main scope of the LM technique is to at least maintain the accuracy of low speed regions without introducing artefacts and hampering the global solution and stability of the numerical scheme. Two families of spatial schemes are considered within the k-exact FV framework: the Monotonic Upstream-Centered Scheme for Conservation Laws (MUSCL) and the Weighted Essentially Non-Oscillatory (WENO). The simulations are advanced in time with an explicit third-order Strong Stability Preserving (SSP) Runge-Kutta method. Several flow problems are considered for inviscid and turbulent flows where the obtained solutions are compared with referenced data. The associated benefits of the method are analysed in terms of overall accuracy, dissipation characteristics, order of scheme, spatial resolution and grid composition.

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“…In this study, we employ the fifth order WENO scheme developed by Matsuyma. 23 Matsuyama used the recently developed WENO scheme for the interpolation of the values at cell interfaces based on the finite volume method. The Thornber's correction 26 is utilized for further reducing numerical dissipation.…”

Section: Methodsmentioning

confidence: 99%

LES Computation of Turbulent Heat Flux on Reentry Capsule Afterbody with Forced Transition

Ishihara

Ogino²,

Ohnishi³

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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A high order CFD code was developed for LES computation of turbulent heat flux in hypersonic flow. Aeroheating measurement tests with forced transition on an Apollo capsule model and an HTV-R which was a manned space capsule under development by JAXA were performed by the free-piston shock tunnel HIEST in JAXA Kakuda Space Center. Measured data set indicate that heat flux on the forebody of the Apollo capsule model was 1.5-2 times larger than one in laminar flow. On the other hand, the heat flux on the afterbody of HTV-R became significantly larger. Furthermore, in the separation region which exists afterbody of capsules, the Baldwin-Lomax model which can reproduce turbulent heat flux in the attached flow, tends to underestimate. In order to reproduce the turbulent heat flux on the after body by numerical simulation, high order CFD code towards LES in hypersonic flow is needed. Since the robustness near the shock and high resolution in the boundary layer is needed for LES in hypersonic flow, improved WENO method is employed. We calculated the hypersonic flow (M∞ = 17) around cylinder and investigated the robustness for strong shock by the method. Smooth pressure distribution was obtained agree well with the calculated heat flux by NASA LAURA code. Our developed code applied to the hypersonic flowfield around HTV-R with a trip and the heat flux was examined.

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Performance of all-speed AUSM-family schemes for DNS of low Mach number turbulent channel flow

Abstract: This article examines the performance of all-speed AUSM-family schemes in predicting low

Cited by 25 publications

References 32 publications

Hybridized SLAU2–HLLI and hybridized AUSMPW$$+$$–HLLI Riemann solvers for accurate, robust, and efficient magnetohydrodynamics (MHD) simulations, part I: one-dimensional MHD

Hybridized SLAU2–HLLI and hybridized AUSMPW$$+$$–HLLI Riemann solvers for accurate, robust, and efficient magnetohydrodynamics (MHD) simulations, part I: one-dimensional MHD

Low-Mach number treatment for Finite-Volume schemes on unstructured meshes

LES Computation of Turbulent Heat Flux on Reentry Capsule Afterbody with Forced Transition

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