DOCSLIB.ORG

Time Integration Methods for Compressible Flow

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Time Integration Methods for Compressible Flow TIME INTEGRATION METHODS FOR COMPRESSIBLE FLOW PROEFSCHRIFT ter verkrijging van de graad van doctor aan de Universiteit Twente, op gezag van de rector magnificus, prof. dr. F.A. van Vught, volgens besluit van het College voor Promoties in het openbaar te verdedigen op vrijdag 24 september 1999 te 15.00 uur door Ren´evanBuuren geboren op 14 april 1972 te Leeuwarden Dit proefschrift is goedgekeurd door de promotor prof. dr. ir. P.J. Zandbergen en de assistent-promotor dr. J.G.M. Kuerten aan mijn ouders Buuren, Ren´evan Time integration methods for compressible flow Thesis Universiteit Twente, Enschede. -Withref.-WithsummaryinDutch. ISBN 90-36513243 Copyright c 1999 by R. van Buuren ! Faculty of Mathematical Sciences University of Twente P.O. Box 217 7500 AE Enschede The Netherlands Contents 1Introduction 1 1.1 Turbulence............................... 1 1.2 Time integration . 5 1.2.1 Numerical example . 7 1.2.2 Relevant types of flow for implicit methods . 7 1.2.3 Efficiencyofimplicitschemes. 9 1.3 Outlineofthisthesis ......................... 11 2Numericalmethods 15 2.1 Introduction.............................. 15 2.2 Numericalrequirements ....................... 16 2.3 Spatial Discretisation . 20 2.3.1 Inviscidterms ......................... 20 2.3.2 Viscous terms . 25 2.4 Time integration . 26 2.4.1 Explicit time integration . 26 2.4.2 Implicit time integration . 27 2.4.3 TVD-property . 29 2.5 Linear solvers . 31 2.5.1 Basic iterative methods . 32 2.5.2 Krylovmethods ........................ 33 2.6 Multigrid . 35 2.6.1 Two-grid model . 35 3 The shock tube 39 3.1 Introduction.............................. 39 3.2 Governing equations and problem definition . 39 3.3 Spatial discretisation . 40 3.4 Approximation of the Jacobi matrix . 41 3.4.1 Numerical approximation of the flux Jacobi matrix . 42 v vi CONTENTS 3.4.2 Numerical flux Jacobi matrix . 43 3.5 Numericalresults ........................... 43 3.5.1 Numerical solution . 44 3.5.2 Comparison of linear solvers . 47 3.6 Entropy production . 50 3.6.1 Entropy satisfying solutions . 51 3.6.2 Application to the Euler equations . 52 3.7 Conclusions . 56 4Inviscidflowaroundanairfoil 59 4.1 Introduction.............................. 59 4.2 Governing equations and explicit numerical method . 61 4.2.1 Governing equations . 61 4.2.2 Spatial discretisation . 61 4.2.3 Explicit time integration . 63 4.2.4 Boundary conditions . .................... 63 4.3 Numericalresults ........................... 64 4.4 Implicitmethod............................ 67 4.5 Numericalresultsfortheimplicitscheme. 68 4.5.1 Grid refinement . 73 4.5.2 Linear Stability Theory .................... 74 4.6 Conclusions . 76 5Accelerationtechniquesforsteadyflowcomputations79 5.1 Introduction.............................. 79 5.2 Multigrid acceleration . .................... 81 5.3 Parallelization . 83 5.3.1 Domain decomposition . 85 5.3.2 Numerical results . 86 5.4 Conclusions . 92 6Shockboundary-layerinteractionflow 95 6.1 Introduction.............................. 95 6.2 Governing equations and explicit numerical method . 97 6.2.1 Governing equations . 98 6.2.2 Spatial discretisation . 99 6.2.3 Boundary conditions . .................... 99 6.2.4 Explicit time integration . 101 6.3 Explicitnumericalreferenceresults . 102 6.4 Implicit time integration method . 104 6.4.1 Time integration and implicit approximation of the flux . 106 CONTENTS vii 6.4.2 Implicit treatment of boundary conditions . 108 6.4.3 Linear solver . 110 6.5 Implicit time integration results . 110 6.5.1 Error bounds . .................... 110 6.5.2 Comparison with explicit results . 113 6.6 Dynamical behavior for large time steps . 117 6.7 Conclusions . 121 7Analysisofmultigridperformanceforunsteadyflow123 7.1 Introduction . 123 7.2 Identification of test case . 125 7.3 Multigrid applied to unsteady flow . 127 7.3.1 Damping characteristics flat plate . 128 7.3.2 Changing the smoother . 132 7.4 Model equation . 133 7.5 Conclusions . 137 8Partiallyimplicittimeintegrationschemes 139 8.1 Introduction . 139 8.2 Mixed multi-stage schemes . 141 8.2.1 Second order multi-stage schemes . 141 8.3 Steady-state-consistency . 143 8.3.1 Model equation . 144 8.3.2 Steady-state-consistent schemes . 145 8.4 Stability . ........................... 146 8.4.1 M-stable schemes . 146 8.4.2 Stability of steady-state-consistent schemes . 148 8.5 Numerical results and implementation . 151 8.5.1 Implementation . 151 8.5.2 Numerical results . 152 8.5.3 Convergence characteristics . 155 8.5.4 High aspect ratio . 158 8.6 Conclusions . 159 9Adynamicaltimestepcriterion 163 9.1 Introduction . 163 9.2 Proper orthogonal decomposition . .......... 164 9.3 Numerical results . 166 9.4 Conclusions . 171 10 Conclusions 173 viii CONTENTS Bibliography 175 Summary 184 Samenvatting 187 Dankwoord 190 Over de schrijver 191 Chapter 1 Introduction Iamanoldmannow,andwhenIdieandgotoheaventherearetwomatters on which I hope for enlightenment. One is quantum electrodynamics, and the other is the turbulent motion of fluids. And about the former I am rather optimistic 1. 1.1 Turbulence In both nature and technological applications the flow of fluids plays an im- portant role. Consider e.g. an airplane: important properties as lift and drag are completely determined by the flow of air around the airplane. As a sec- ond example the mixing of fuel and oxygen in an internal combustion engine determines much of the efficiency of the engine and the emission of gases into the environment. In our bodies blood runs through our veins, and we breath air in and out of our lungs. Or consider the motion of gases in the atmo- sphere and the flow of water in lakes and seas and their relevance to weather prediction [30, 44, 64]. In all these cases turbulence plays an important role and depending on the situation turbulence has beneficial or detrimental ef- fects. Obviously, a detailed investigation of the dominant flow mechanisms is essential in order to understand these systems or to optimize certain specific properties. Roughly speaking there are two characteristic types of flow, i.e. laminar flow and turbulent flow. Laminar flow displays smooth and gradual changes in time and space, whereas turbulent flow behaves chaotic with rapid changes in time and space. An every-day example of these two types of flow can be found if one observes the flow from a water tap [64]. If the tap is opened slightly the 1Reportedly said by Sir Horace Lamb in an address to the British Association for the Advancement of Physics in 1932 [64]. 1 2 CHAPTER 1 water comes out in a smooth current, characterizing laminar flow. However, if the tap is fully opened the water flow becomes more vivid, characterizing turbulent flow. In general a flow of a Newtonian fluid is mathematically described by the Navier-Stokes equations which are a set of coupled nonlinear partial differential equations combining the physical laws of conservation of mass, momentum and energy (see Eq. 6-1). By non-dimensionalising the Navier-Stokes equations it appears that a flow of a calorically perfect gas can be compactly characterized by four dimensionless numbers: (γ,Pr,Re,M). The adiabatic gas constant γ and the Prandtl number, Pr,dependonthetypeoffluid.Formanyfluids these are experimentally determined which leaves the Mach number, M,and the Reynolds number, Re still to be specified. The Mach number, which is the ratio of the speed of the fluid and the speed of sound, is related to compressibility, i.e. density variations, of the fluid. For low Mach number the fluid is nearly incompressible (e.g. constant density) like e.g. water in about all applications, while for high Mach number flow of e.g. gases typical compressible phenomena such as shock waves can occur. The Reynolds number is the ratio of inertia and viscous effects and is related to the two characteristic types of flow described earlier. For low Reynolds number the flow is laminar whereas it becomes turbulent if a critical (flow dependent) Reynolds number is exceeded. In this century a lot of effort has been put into understanding turbulence and the phenomena which trigger turbulence. Next to theoretical develop- ments and experiments, computer capacity has increased enormously in the past two decades which enables simulations of flows of increasing complexity. However, on the whole only a few substantial advances appear to have been made. For a short and comprehensible review we refer to [30]. Here we only focus on some aspects related to computational effort associated with flow simulations and for more details we refer to Refs. [30, 44, 85] and references therein. One of the assumptions on turbulence is that turbulent flows are hierarchical and involve a broad spectrum of so-called eddies. The largest eddies are produced by the driving forces of the flow, which in turn break into smaller eddies and this process continues until the resulting eddies reach asizeonwhichmolecularviscosityconvertstheeddymotionintoheat.The property of this energy cascade from large to small eddies is predicted by Kol- mogorov [51] and is expected to hold universally. In the Kolmogorov theory of turbulent flow the ratio of the lengths of the largest and smallest eddies is of the order Re3/4 which in three dimensions results in a number of degrees of freedom in the order of Re9/4. With this prediction of the number of degrees of freedom it is possible to roughly estimate the computational cost for simulating turbulent flow. If Introduction 3 Z X Y Figure 1-1: Surface triangulation of a generic fighter configuration; Technology demonstration of the FASTFLO CFD system (courtesy of NLR, Amsterdam). 4 CHAPTER 1 aturbulentflowistobesimulatedwithacomputerthecontinuousspaceis approximated by a discrete grid on which the flow quantities are determined. The grid size has to be fine enough to resolve all relevant eddies. This means that on the order of Re9/4 grid points are required. If we assume that the amount of work is proportional to the number of grid points this means that the required CPU (central processor unit) time is also of the same order. For turbulent flows which typically have large Reynolds numbers the problem is obvious.
Load more

Recommended publications
  • A Truncation Error Analysis of Third-Order MUSCL Scheme for Nonlinear Conservation Laws
    A Truncation Error Analysis of Third-Order MUSCL Scheme for Nonlinear Conservation Laws Hiroaki Nishikawa∗ National Institute of Aerospace, Hampton, VA 23666, USA Abstract This paper is a rebuttal to the claim found in the literature that the MUSCL scheme cannot be third-order accurate for nonlinear conservation laws. We provide a rigorous proof for third-order accuracy of the MUSCL scheme based on a careful and detailed truncation error analysis. Throughout the analysis, the distinction between the cell average and the point value will be strictly made for the numerical solution as well as for the target operator. It is shown that the average of the solutions reconstructed at a face by Van Leer’s κ-scheme recovers a cubic solution exactly with κ = 1/3, the same is true for the average of the nonlinear fluxes evaluated by the reconstructed solutions, and a dissipation term is already sufficiently small with a third-order truncation error. Finally, noting that the target spatial operator is a cell-averaged flux derivative, we prove that the leading truncation error of the MUSCL finite-volume scheme is third-order with κ = 1/3. The importance of the diffusion scheme is also discussed: third-order accuracy will be lost when the third-order MUSLC scheme is used with a wrong fourth-order diffusion scheme for convection-diffusion problems. Third-order accuracy is verified by thorough numerical experiments for both steady and unsteady problems. This paper is intended to serve as a reference to clarify confusions about third-order accuracy of the MUSCL scheme, as a guide to correctly analyze and verify the MUSCL scheme for nonlinear equations, and eventually as the basis for clarifying third-order unstructured-grid schemes in a subsequent paper.
    [Show full text]
  • The QUICK Scheme Is a Third-Order Finite-Volume Scheme with Point
    The QUICK Scheme is a Third-Order Finite-Volume Scheme with Point-Valued Numerical Solutions Hiroaki Nishikawa∗ National Institute of Aerospace, Hampton, VA 23666, USA June 30, 2020 Abstract In this paper, we resolve the ever-present confusion over the QUICK scheme: it is a second-order scheme or a third-order scheme. The QUICK scheme, as proposed in the original reference [B. P. Leonard, Comput. Methods. Appl. Mech. Eng., 19, (1979), 59-98], is a third-order (not second-order) finite-volume scheme for the integral form of a general nonlinear conservation law with point-valued solutions stored at cell centers as numerical solutions. Third-order accuracy is proved by a careful and detailed truncation error analysis and demonstrated by a series of thorough numerical tests. The QUICK scheme requires a careful spatial discretization of a time derivative to preserve third-order accuracy for unsteady problems. Two techniques are discussed, including the QUICKEST scheme of Leonard. Discussions are given on how the QUICK scheme is mistakenly found to be second-order accurate. This paper is intended to serve as a reference to clarify any confusion about third-order accuracy of the QUICK scheme and also as the basis for clarifying economical high-order unstructured- grid schemes as we will discuss in a subsequent paper. 1 Introduction This paper is a sequel to the previous paper [1], where we discussed the third-order MUSCL scheme. The main motivation behind this work is to clarify some economical high-order unstructured-grid finite-volume schemes used in practical computational fluid dynamics solvers but largely confused in their mechanisms to achieve third- and possibly higher-order accuracy (e.g., third-order U-MUSCL with κ =1/2 [2], κ =1/3 [3, 4], κ = 0 [5, 6]).
    [Show full text]
  • Finite-Volume Simulations of Maxwell's Equations On
    Finite-Volume Simulations of Maxwell's Equations on Unstructured Grids Ian Jeffrey PhD Thesis Submitted in Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy Department of Electrical and Computer Engineering University of Manitoba Winnipeg, Manitoba, Canada Copyright c 2011 by Ian Jeffrey Abstract Herein a fully parallel, upwind and flux-split Finite-Volume Time-Domain (FVTD) numerical engine for solving Maxwell's Equations on unstructured grids is developed. The required background theory for solving Maxwell's Equations using FVTD is given in sufficient detail, including a description of both the temporal and spatial approx- imations used. The details of the local-time stepping strategy of Fumeaux et al. is included. A global mesh-truncation scheme using field integration over a Huygens' surface is also presented. The capabilities of the FVTD algorithm are augmented with thin-wire and subcell circuit models that permit very flexible and accurate simulations of circuit-driven wire structures. Numerical and experimental validation shows that the proposed models have a wide-range of applications. Specifically, it appears that the thin-wire and subcell circuit models may be very well suited to the simulation of radio-frequency coils used in magnetic resonance imaging systems. A parallelization scheme for the volumetric field solver, combined with the local-time stepping, global mesh-truncation and subcell models is developed that theoretically provides both linear time- and memory scaling in a distributed parallel environment. Finally, the FVTD code is converted to the frequency domain and the possibility of using different flux-reconstruction schemes to improve the iterative convergence of the Finite-Volume Frequency-Domain algorithm is investigated.
    [Show full text]
  • Méthode De Décomposition De Domaine Avec Adaptation De
    UNIVERSIT E´ PARIS 13 No attribu´epar la biblioth`eque TH ESE` pour obtenir le grade de DOCTEUR DE L’UNIVERSIT E´ PARIS 13 Discipline: Math´ematiques Appliqu´ees Laboratoire d’accueil: ONERA - Le centre fran¸cais de recherche a´erospatiale Pr´esent´ee et soutenue publiquement le 19 d´ecembre 2014 par Oana Alexandra CIOBANU Titre M´ethode de d´ecomposition de domaine avec adaptation de maillage en espace-temps pour les ´equations d’Euler et de Navier–Stokes devant le jury compos´ede: Fran¸cois Dubois Rapporteur Laurence Halpern Directrice de th`ese Rapha`ele Herbin Rapporteure Xavier Juvigny Examinateur Olivier Lafitte Examinateur Juliette Ryan Encadrante UNIVERSITY PARIS 13 THESIS Presented for the degree of DOCTEUR DE L’UNIVERSIT E´ PARIS 13 In Applied Mathematics Hosting laboratory: ONERA - The French Aerospace Lab presented for public discussion on 19 decembre 2014 by Oana Alexandra CIOBANU Subject Adaptive Space-Time Domain Decomposition Methods for Euler and Navier–Stokes Equations Jury: Fran¸cois Dubois Reviewer Laurence Halpern Supervisor Rapha`ele Herbin Reviewer Xavier Juvigny Examiner Olivier Lafitte Examiner Juliette Ryan Supervisor newpage Remerciements Tout d’abord, je remercie grandement Juliette Ryan pour avoir accept´e d’ˆetre mon encad- rante de stage puis mon encadrante de th`ese. Pendant plus de trois ans, elle m’a fait d´ecouvrir mon m´etier de jeune chercheuse avec beaucoup de patience et de professionnalisme. Elle m’a soutenue, elle a ´et´ed’une disponibilit´eet d’une ´ecoute extraordinaires, tout en sachant ˆetre rigoureuse et exigeante avec moi comme avec elle-mˆeme. Humainement, j’ai beaucoup appr´eci´e la relation d’amiti´eque nous avons entretenue, le climat de confiance que nous avons maintenu et les discussions extra-math´ematiques que nous avons pu avoir et qui ont renforc´ele lien que nous avions.
    [Show full text]
  • A Comparison of High-Resolution, Finite-Volume, Adaptive±Stencil
    Advances in Water Resources 24 (2001) 29±48 www.elsevier.com/locate/advwatres A comparison of high-resolution, ®nite-volume, adaptive±stencil schemes for simulating advective±dispersive transport Matthew W. Farthing, Cass T. Miller * Department of Environmental Sciences and Engineering, Center for the Advanced Study of the Environment, University of North Carolina, Chapel Hill, NC 27599-7400, USA Received 1 February 2000; received in revised form 8 May 2000; accepted 16 May 2000 Abstract We investigate a set of adaptive±stencil, ®nite-volume schemes used to capture sharp fronts and shocks in a wide range of ®elds. Our objective is to determine the most promising methods available from this set for solving sharp-front advective±dispersive transport problems. Schemes are evaluated for a range of initial conditions, and for Peclet and Courant numbers. Based upon results from this work, we identify the most promising schemes based on eciency and robustness. Ó 2000 Elsevier Science Ltd. All rights reserved. 1. Introduction ecient for solving relatively simple advective-domi- nated problems. These approaches, however, can pose The processes of solute and energy transport in nat- mass conservation problems, are not well suited for ural systems are most often described using an advec- problems with multiple sources and non-linear mass tive±dispersive equation (ADE) with additional terms transfer terms, and can be diusive and oscillatory for sources, reactions, and interphase exchange of mass [3,19,38,44]. or energy [34]. For many problems, especially those in- Over the last decade, simulators in the water re- volving multiple species, ADE solutions can be a sub- sources ®eld have employed so-called high-resolution stantial part of the computational eort involved for a methods more and more for discretizing the advective given ¯ow and transport simulator.
    [Show full text]
  • New Roe Scheme for All Speed Flow
    Role of Momentum Interpolation Mechanism of the Roe Scheme in Shock Instability Xiao-dong Ren1,2 Chun-wei Gu1 Xue-song Li1,* 1. Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering, Tsinghua University, Beijing 100084, PR China 2. Department of Mathematics, School of Science, Hong Kong University of Science and Technology, Hong Kong, China Abstract: The shock instability phenomenon is a famous problem for the shock-capturing scheme. By subdividing the numerical dissipation of the Roe scheme, the pressure-difference-driven modification for the cell face velocity is regarded as a version of the momentum interpolation method (MIM). The MIM is necessary for low Mach number flows to suppress the pressure checkerboard problem. Through the analysis and numerical tests, MIM has been discovered to have the most important function in shock instability. In fact, MIM should be completely removed for non-linear flows. However, unexpected MIM is activated on the cell face nearly parallel to the flow for high Mach number flows or low Mach number flows in shock. Therefore, the MIM should be kept for low Mach number flows and be completely removed for high Mach number flows and low Mach number flows in shock. For such conditions, two coefficients are designed on the basis of the local Mach number and a shock detector. The improved Roe scheme is then proposed. This scheme considers the requirement of MIM for incompressible and compressible flows and is validated for good performance of numerical tests. It is also proved that the acceptable result can be obtained with only Mach number coefficient for general practical computation.
    [Show full text]
  • Second-Order MUSCL Schemes Based on Dual Mesh Gradient Reconstruction \(DMGR\)
    ESAIM: M2AN 48 (2014) 583–602 ESAIM: Mathematical Modelling and Numerical Analysis DOI: 10.1051/m2an/2013105 www.esaim-m2an.org SECOND-ORDER MUSCL SCHEMES BASED ON DUAL MESH GRADIENT RECONSTRUCTION (DMGR) Christophe Berthon1, Yves Coudiere` 2,3 and Vivien Desveaux1 Abstract. We discuss new MUSCL reconstructions to approximate the solutions of hyperbolic systems of conservations laws on 2D unstructured meshes. To address such an issue, we write two MUSCL schemes on two overlapping meshes. A gradient reconstruction procedure is next defined by involving both approximations coming from each MUSCL scheme. This process increases the number of numerical unknowns, but it allows to reconstruct very accurate gradients. Moreover a particular attention is paid on the limitation procedure to enforce the required robustness property. Indeed, the invariant region is usually preserved at the expense of a more restrictive CFL condition. Here, we try to optimize this condition in order to reduce the computational cost. Mathematics Subject Classification. 65M12, 35L65, 76M12. Received July 5, 2012. Revised May 24, 2013. Published online January 20, 2014. 1. Introduction The present work is devoted to the numerical approximation of the weak solutions of nonlinear hyperbolic systems of conservation laws in two dimensions. The system under consideration reads 2 ∂tw + ∂xf(w)+∂yg(w)=0,t≥ 0, (x, y) ∈ R , (1.1) where w : R+ × R2 → Ω stands for the unknown state vector. Here, Ω ⊂ Rd denotes the well-known set of admissible states and is assumed to be convex. Concerning the flux functions f,g : Ω → Rd, as usual they are assumed to be smooth enough, at least Lipschitz-continuous.
    [Show full text]
  • A Comparison of Hyperbolic Solvers Ii: Ausm-Type and Hybrid Lax-Wendroff- Lax-Friedrichs Methods for Two-Phase Flows
    Brazilian Journal of Chemical ISSN 0104-6632 Printed in Brazil Engineering www.abeq.org.br/bjche Vol. 27, No. 01, pp. 153 - 171, January - March, 2010 A COMPARISON OF HYPERBOLIC SOLVERS II: AUSM-TYPE AND HYBRID LAX-WENDROFF- LAX-FRIEDRICHS METHODS FOR TWO-PHASE FLOWS R. M. L. Coelho1*, P. L. C. Lage2 and A. Silva Telles1 1Curso de Pós-Graduação em Tecnologia de Processos Químicos e Bioquímicos (TPQB), Departamento de Engenharia Química, Escola de Química, Bloco E, Centro de Tecnologia, Universidade Federal do Rio de Janeiro, CEP: 21949-900, Rio de Janeiro - RJ, Brazil. 2Programa de Engenharia Química, COPPE, Universidade Federal do Rio de Janeiro, P.O. Box 68502, CEP: 21945-970, Rio de Janeiro - RJ, Brazil. *Current address: Research and Development Center (PETROBRAS /CENPES/EB-E&P/EPEP), Phone: + (55) (21) 3865-7406, Fax: + (55) (21) 3865-6793, Cidade Universitária, Q.7, Ilha do Fundão, CEP: 21949-900, Rio de Janeiro - RJ, Brazil. E-mail: [email protected] (Submitted: October 23, 2008 ; Revised: October 30, 2009 ; Accepted: January 4, 2010) Abstract - Riemann-solver based schemes are difficult and sometimes impossible to be applied for complex flows due to the required average state. Other methods that do not use Riemann-solvers are best suited for such cases. Among them, AUSM+, AUSMDV and the recently proposed Hybrid Lax-Friedrichs-Lax-Wendroff (HLFW) have been extended to two-phase flows. The eigenstructure of the two-fluid model is complex due to the phase interactions, leading to numerous numerical difficulties. One of them is the well-posedness of the equation system because it may lose hyperbolicity.
    [Show full text]
  • Test Cases for Grid-Based Direct Kinetic Modeling of Plasma Flows
    Plasma Sources Science and Technology PAPER Related content - Numerical analysis of azimuthal rotating Test cases for grid-based direct kinetic modeling spokes in a crossed-field discharge plasma of plasma flows R Kawashima, K Hara and K Komurasaki - Hollow cathode modeling: I. A coupled plasma thermal two-dimensional model To cite this article: Kentaro Hara and Kyle Hanquist 2018 Plasma Sources Sci. Technol. 27 065004 Gaétan Sary, Laurent Garrigues and Jean- Pierre Boeuf - Sheaths in laboratory and space plasmas Scott Robertson View the article online for updates and enhancements. Recent citations - Interaction of biased electrodes and plasmas: sheaths, double layers, and fireballs Scott D Baalrud et al - Ion kinetics and nonlinear saturation of current-driven instabilities relevant to hollow cathode plasmas Kentaro Hara and Cameron Treece - An overview of discharge plasma modeling for Hall effect thrusters Kentaro Hara This content was downloaded from IP address 150.135.159.43 on 05/01/2021 at 00:18 Plasma Sources Science and Technology Plasma Sources Sci. Technol. 27 (2018) 065004 (14pp) https://doi.org/10.1088/1361-6595/aac6b9 Test cases for grid-based direct kinetic modeling of plasma flows Kentaro Hara1 and Kyle Hanquist2 1 Texas A&M University, College Station, Texas, United States of America 2 University of Michigan, Ann Arbor, Michigan, United States of America E-mail: [email protected] Received 19 January 2018, revised 1 May 2018 Accepted for publication 22 May 2018 Published 18 June 2018 Abstract Grid-based kinetic models are promising in that the numerical noise inherent in particle-based methods is essentially eliminated. Here, we call such grid-based techniques a direct kinetic (DK) model.
    [Show full text]
  • The C-MUSCL Scheme, a High Order Finite Volume Method with Constrained Transport for Astrophysical MHD
    Master's Thesis The C-MUSCL Scheme, a High Order Finite Volume Method with Constrained Transport for astrophysical MHD Lukas Knosp September 23, 2019 Supervisor: Associate Professor Dr. Ralf Kissmann Institute for Astro- and Particle Physics Contents Statutory Declaration4 I. Astrophysical Plasmas6 1. From Kinetic Theory to Magnetohydrodynamics7 2. Equations and Notations 12 2.1. Euler System . 13 2.1.1. Alternative Formulation . 13 2.2. Induction System . 14 II. Numerical Methods 16 3. Introduction 17 4. Theory of Hyperbolic Conservation Laws 19 4.1. Linear Conservation Laws . 19 4.1.1. Linear Scalar Advection . 19 4.1.2. Linear Hyperbolic Systems . 22 4.2. Non-linear Conservation Laws . 25 4.2.1. Burgers' Equation . 26 4.2.2. Non-linear Systems . 30 5. Finite Volume Methods 33 5.1. Conservative Schemes . 33 5.2. Godunov'sMethod .............................. 36 5.3. The HLL Approximate Riemann Solver . 38 5.4. High-Order Godunov-type Methods . 39 5.4.1. Reconstruction . 40 5.4.2. Semi-Discrete Schemes . 43 5.4.3. MUSCL-Hancock-Method . 44 5.5. Finite Volume Methods in Three Dimensions . 47 5.5.1. Conservative Schemes . 47 5.5.2. High-Order Schemes in Multiple Space Dimensions . 48 2 6. Treatment of the Magnetic Field 50 6.1. Constrained Transport . 51 6.1.1. High-Order Variation . 54 6.2. C-MUSCL Scheme . 55 III. Implementation 58 7. The CRONOS-Code 59 7.1. CodeStructure ................................ 59 7.2. Adapting the Code . 61 8. Verification & Results 63 8.1. One-dimensional Tests . 63 8.1.1. SodShock-Tube............................ 63 8.1.2.
    [Show full text]
  • An Efficient High-Resolution Shock-Capturing Scheme for Multi
    Chin. J. Astron. Astrophys. Vol. 6 (2006), No. 6, 680–688 Chinese Journal of (http://www.chjaa.org) Astronomy and Astrophysics An Efficient High-Resolution Shock-Capturing Scheme for Multi-Dimensional Flows I. Hydrodynamics ∗ Cong Yu 1 National Astronomical Observatories / Yunnan Astronomical Observatory, Chinese Academy of Sciences, Kunming 650011; [email protected] 2 Graduate School of Chinese Academy of Sciences, Beijing 100049 Received 2006 February 27; accepted 2006 April 17 Abstract Many problems at the forefront of theoretical astrophysics require a treatment of dynamical fluid behavior. We present an efficient high-resolution shock-capturing hydrody- namic scheme designed to study such phenomena. We have implemented a weighted, essen- tially non-oscillatory (WENO) scheme to fifth order accuracy in space. HLLE approximate Riemann solver is used for the flux computation at cell interface, which does not require spectral decomposition into characteristic waves and so is computationally friendly. For time integration we apply a third order total variation diminishing (TVD) Runge-Kutta scheme. Extensive testing and comparison with schemes that require characteristic decomposition are carried out demonstrating the ability of our scheme to address challenging open questions in astrophysics. Key words: accretion — hydrodynamics — method: numerical — shock waves 1 INTRODUCTION High-resolution shock-capturing methods of the Godunov type have been successfully applied to various as- trophysical problems in the last decade (Mellema, Eulderink
    [Show full text]
  • Romain Teyssier
    The RAMSES code and related techniques I. Hydro solvers Romain Teyssier HIPACC 2010 Romain Teyssier Outline - The Euler equations - Systems of conservation laws - The Riemann problem - The Godunov Method - Riemann solvers - 2D Godunov schemes - Second-order scheme with MUSCL - Slope limiters and TVD schemes - 2D slope limiter. HIPACC 2010 Romain Teyssier The Euler equations in conservative form A system of 3 conservation laws The vector of conservative variables HIPACC 2010 Romain Teyssier The Euler equations in primitive form A non-linear system of PDE (quasi-linear form) The vector of primitive variables We restrict our analysis to perfect gases HIPACC 2010 Romain Teyssier The isothermal Euler equations Conservative form with conservative variables Primitive form with primitive variables a is the isothermal sound speed HIPACC 2010 Romain Teyssier Systems of conservation laws General system of conservation laws with F flux vector. Examples: 1- Isothermal Euler equations 2- Euler equation 3- Ideal MHD equations HIPACC 2010 Romain Teyssier Primitive variables and quasi-linear form We define the Jacobian of the flux function as: The system writes in the quasi-linear (non-conservative) form We define the primitive variables and the Jacobian of the transformation The system writes in the primitive (non-conservative) form The matrix A is obtained by The system is hyperbolic if A or J have real eigenvalues. HIPACC 2010 Romain Teyssier The advection equation Scalar (one variable) linear (u=constant) partial differential equation (PDE) Initial conditions: Define the function: Using the chain rule, we have: is a Riemann Invariant along the characteristic curves defined by t x HIPACC 2010 Romain Teyssier The isothermal wave equation We linearize the isothermal Euler equation around some equilibrium state.
    [Show full text]