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2009, Springer eBooks
A Mach-uniform algorithm is an algorithm with a good convergence rate for any level of the Mach number. In this paper, the severe time step restriction for low speed flows is removed by treating the acoustic and diffusive terms implicitly. After identification of these terms in the conservative set, we end up with a semi-implicit system. The way to solve this system can be chosen. Three different solution techniques are presented: a fully coupled algorithm, the coupled pressure and temperature correction algorithm [K. Nerinckx, J. Vierendeels, E. Dick, Mach-uniformity through the coupled pressure and temperature correction algorithm, Journal of Computational Physics 206 (2005) 597-623], and a fully segregated pressure-correction algorithm. We analyse the convergence behavior of the considered algorithms for some typical flow problems. Moreover, a Fourier stability analysis is done. For inviscid flow, the fully segregated and the fully coupled algorithm need about as much time steps to reach steady state. Therefore, the more segregation is introduced, the faster the calculation can be done. In case of heat transfer, the fully segregated pressure-correction algorithm suffers from a diffusive time step limit. This is not the case for the semi-segregated coupled pressure and temperature correction algorithm. Finally, when the gravity terms play an important role, only the fully coupled algorithm can avoid an additional time step restriction.
Journal of Computational Physics, 2005
We present a new type of algorithm: the coupled pressure and temperature correction algorithm. It is situated in between the fully coupled and the fully segregated approach, and is constructed such that Mach-uniform accuracy and efficiency are obtained. The essential idea is the separation of the convective and the acoustic/thermodynamic phenomena: a convective predictor is followed by an acoustic/thermodynamic corrector. For a general case, the corrector consists of a coupled solution of the energy and the continuity equations for both pressure and temperature corrections. For the special case of an adiabatic perfect gas flow, the algorithm reduces to a fully segregated method, with a pressure-correction equation based on the energy equation. Various test cases are considered, which confirm that Mach-uniformity is obtained.
International Journal for Numerical Methods in Fluids, 2012
In the present work, we propose a reformulation of the fluxes and interpolation calculations in the PISO method, a well-known pressure-correction solver. This new reformulation introduces the AUSM C up flux definition as a replacement for the standard Rhie and Chow method of obtaining fluxes and central interpolation of pressure at the control volume faces. This algorithm tries to compatibilize the good efficiency of a pressure based method for low Mach number applications with the advantages of AUSM C up at high Mach number flows. The algorithm is carefully validated using exact solutions. Results for subsonic, transonic and supersonic axisymmetric flows in a nozzle are presented and compared with exact analytical solutions. Further, we also present and discuss subsonic, transonic and supersonic results for the well known bump test-case. The code is also benchmarked against a very tough test-case for the supersonic and hypersonic flow over a cylinder. Thakur and Wright [9] have applied their compressible pressure methods to complex geometries such as compressors and gas turbines.
Journal of Computational and Applied Mathematics, 2008
We focus on the construction of Mach-uniform algorithms. The basic idea is to remove the severe time step restrictions for low speed flows, by treating the acoustic terms implicitly. The way to solve the obtained semi-implicit system can be chosen. Three different solution techniques are presented, varying between a fully coupled algorithm and a fully segregated pressure correction algorithm. We show that the number of time steps to reach steady state is comparable for the fully coupled as well as the fully segregated method. Therefore, the more segregation is introduced, the more efficient the calculation can be done.
International Journal for Numerical Methods in Fluids, 2000
An algorithm for the simulation of unsteady, viscous, stratified compressible flows, which remains valid at all speeds, is presented. The method is second-order accurate in both space and time and is independent of the Mach number. In order to remove the stiffness of the numerical problem due to the large disparity between the flow speed and the acoustic wave speed at low Mach number, an approximate Newton method, based on artificial compressibility, is proposed. Additionally, a modified advection upstream splitting method (AUSM +) scheme is used, which permits accurate computations of both compressible and incompressible flows. A detailed description of the method and an efficiency comparison with other approximate Newton methods described in the literature are given. Furthermore, it is shown that the accuracy of the algorithm is not dependent on the Mach number through the computations of various benchmark test cases. I. MARY, P. SAGAUT, AND M. DEVILLE 372 transient behavior of the Navier -Stokes equations is modified. The main difficulty in solving the compressible, unsteady equations at a low Mach number is due to the large disparity between the acoustic wave speed and the advection velocity. Therefore, an implicit temporal discretization must be used otherwise a severe stability restriction results on the time step. This is due to the fact that numerical stability considerations impose small time steps on the acoustic waves, while the physics is mainly driven by the main flow, where the time scale is large. Only three kinds of implicit methods that preserve the possibility of unsteady applications at all speeds are described in the literature. The first one, which is at most second-order accurate in time, is based on Strang's splitting [5] of the Navier-Stokes equations into two sub-systems. One sub-system contains the acoustic part, where an implicit method is used for the integration, and the other is integrated by an explicit scheme. Erlebacher et al. successfully used this technique to compute isotropic homogeneous turbulence at low Mach numbers. However, the extension to non-homogeneous flow conditions is not straightforward and very few attempts have been reported . The second approach, which is only first-order accurate in time, is based on an extension of projection methods to compressible flows . Finally, the third method is built on dual-time stepping integration procedures .
SUMMARY In this paper, we propose a computational algorithm for the solution of thermally coupled flows in subsonic regime. The formulation is based upon the compressible Navier–Stokes equations, written in nonconserva-tion form. An efficient modular implementation is obtained by solving the energy equation separately and then using the computed temperature as a known value in the momentum-continuity system. If an explicit single-step time integration scheme for the energy equation is used, the decoupling results to be natural. Integration of the momentum-continuity system is carried out using a semi-explicit method, combining Runge–Kutta and Backward Euler schemes for the momentum and continuity equations, respectively. Implicit treatment of pressure leads to favorable time step estimates even in the low Mach number (Ma 1) regimes. The numerical dissipation introduced by the Backward Euler scheme ensures absence of the spurious high frequencies in the numerical solution. The key point of the method is the assumption of linear variation of the temperature within a time step. Combined with a fractional splitting of the momentum-continuity system, it allows to solve the continuity only once per time step. Omitting the necessity of solving for the pressure at every intermediate step of the Runge–Kutta scheme minimizes the computational cost associated to the implicit step and leads to an efficiency close to that of a purely explicit scheme. The method is tested using two benchmark examples.
Journal of Computational and Applied Mathematics, 2013
The proper scaling of the pressure-velocity coupling that arises from the Momentum Interpolation approach for unsteady calculation in low Mach number flow is first identified. Then, it is used to suggest a modification of the AUSM + -up scheme that allows acoustic simulations in low Mach number flow.
Journal of Computational Physics, 2015
An inertia term is introduced in the AUSM +-up scheme. The resulting scheme, called AUSM-IT (IT for Inertia Term), is designed as an extension of the AUSM +-up scheme allowing for full Mach number range calculations of unsteady flows including acoustic features. In line with the continuous asymptotic analysis, the AUSM-IT scheme satisfies the conservation of the discrete linear acoustic energy at first order in the low Mach number limit. Its capability to properly handle low Mach number unsteady flows, that may include acoustic waves or discontinuities, is numerically illustrated. The approach for building the AUSM-IT scheme from the AUSM +-up scheme is applicable to any other Godunov-type scheme.
Numerical Heat Transfer Part B-fundamentals, 2020
The article deals with an implicit formulation of the pressure far field boundary condition, also known as the characteristic boundary condition, in a pressure-based coupled solver. This boundary condition applies to compressible flows over the entire Mach regime, and is derived by invoking the Riemann invariants to implicitly express the flow variables at inlets and outlets in terms of their values inside the domain. A set of inviscid an turbulent flow cases that include pressure far field boundary conditions are tested, namely: low subsonic compressible flow past a NACA0012 airfoil at 10 angle of attack; transonic flow over circular bump; supersonic flow over a series of slender bumps; and DLR-F6 Wing-Body-Nacelle-Pylon Aircraft. Predictions using the prescribed coupled solver are in good agreement with similar results obtained with density-based methods and/or experimental data.
2021
An all-Mach correction is applied to the HLLC scheme for computing liquid flows described by the Euler equations closed with the stiffened gas EoS. The accuracy provided by the corrected scheme is assessed on a series of model problems : Gresho vortex, low-Mach shock tube and a piston problem providing a simplified description of the bubble expansion occurring in some nuclear safety problems.
Journal of Computational and Applied Mathematics, 2018
The method presented below focuses on the numerical approximation of the Euler compressible system. It pursues a twofold objective: being able to accurately follow slow material waves as well as strong shock waves in the context of low Mach number flows. The resulting implicit-explicit fractional step approach leans on a dynamic splitting designed to react to the time fluctuations of the maximal flow Mach number. When the latter rises suddenly, the IMEX scheme, so far driven by a material-wave Courant number, turn into a time-explicit approximate Riemann solver constrained by an acoustic-wave Courant number. It is also possible to enrich the dynamic splitting in order to capture high pressure jumps even when the flow Mach number is low. One-dimensional low Mach number test cases involving single or multiple waves confirm that the present approach is as accurate and efficient as an IMEX Lagrange-Projection method. Besides, numerical results suggest that the stability of the present method holds for any Mach number if the Courant number related to the convective subsystem arising from the splitting is of order unity.
WIT transactions on engineering sciences, 2004
A collocated finite-volume pressure correction procedure for the solution of inviscid compressible flow at all speeds is presented. Pressure correction methods usually adopt a so-called Rhie-Chow interpolation for the cell face velocities in order to provide pressure-velocity coupling. However, as is shown on the testcase of a one-dimensional transonic nozzle, this Rhie-Chow interpolation becomes highly diffusive in high Mach number flows, resulting in an extreme smearing of the shock. Therefore we replace the Rhie-Chow interpolation for velocity and the central interpolation for pressure by AUSM+ definitions. This results in a much sharper shock capturing, even with a first order scheme. However, the diffusive contributions of this flux scale badly when the Mach number diminishes. Furthermore, pressure-velocity coupling at low Mach numbers has to be provided. These two problems can be resolved by respectively introducing a preconditioned speed of sound and adding a pressure-diffusion component. The latter resembles the artificial dissipation introduced by the Rhie-Chow interpolation, but differently it is turned off when sonic values are reached.
Journal of Computational Physics, 2007
When the Mach number tends to zero the compressible Navier-Stokes equations converge to the incompressible Navier-Stokes equations, under the restrictions of constant density, constant temperature and no compression from the boundary. This is a singular limit in which the pressure of the compressible equations converges at leading order to a constant thermodynamic background pressure, while a hydrodynamic pressure term appears in the incompressible equations as a Lagrangian multiplier to establish the divergence-free condition for the velocity. In this paper we consider the more general case in which variable density, variable temperature and heat transfer are present, while the Mach number is small. We discuss first the limit equations for this case, when the Mach number tends to zero. The introduction of a pressure splitting into a thermodynamic and a hydrodynamic part allows the extension of numerical methods to the zero Mach number equations in these non-standard situations. The solution of these equations is then used as the state of expansion extending the expansion about incompressible flow proposed by Hardin and Pope [J.C. Hardin, D.S. Pope, An acoustic/ viscous splitting technique for computational aeroacoustics, Theor. Comput. Fluid Dyn. 6 (1995) 323-340]. The resulting linearized equations state a mathematical model for the generation and propagation of acoustic waves in this more general low Mach number regime and may be used within a hybrid aeroacoustic approach.
Journal of Computational Physics, 2012
Low Mach number flow computation in co-located grid arrangement requires pressurevelocity coupling in order to prevent the checkerboard phenomenon. Two broad categories of pressure-velocity coupling methods for unsteady flows can be distinguished based on the time-step dependency of the coupling coefficient in the definition of the transporting velocity on a face of a control volume. As an example of the time-step independent category, the AUSM +-up scheme is studied. As an example of the second category, Rhie-Chow momentum interpolation methods are studied. Within the momentum interpolation techniques, again two broad categories can be distinguished based on the time-step dependency of the coupling coefficient used for unsteady flow computations, but when a steady state is reached. Variants of Rhie-Chow interpolation methods in each subcategory are studied on critical test cases. The result of the study is that for a good representation of unsteady flows containing acoustic information, the pressure-velocity coupling coefficient must explicitly depend on the time-step, but that the transporting velocity must become independent of the time-step when a steady state is reached.
International Journal for Numerical Methods in Fluids, 2005
ABSTRACT We present a collocated Mach-uniform pressure-correction method. By using a low Mach adapted AUSM+ flux for the spatial discretization, we reach Mach-uniform accuracy. Mach-uniform efficiency is obtained by a pressure-correction equation based on the energy equation. Furthermore, we take heat conduction into account, which as far as we know, has never been done before in the context of Mach-uniform pressure-correction methods. An explicit treatment of the conduction terms results in a diffusive limit on the time step. To avoid this, a coupled solution of the energy equation and the continuity equation is needed. The results for both the adiabatic and the non-adiabatic algorithms are in full accordance with the developed theory. Copyright © 2005 John Wiley & Sons, Ltd.
HAL (Le Centre pour la Communication Scientifique Directe), 2012
geraldine.fjfi.cvut.cz
The work deals with numerical solution of two compressible flows problems. Firstly authors considered steady transonic flows through DCA 8% cascade (Double Circular Arc symmetrical) for increasing upstream Mach numbers M ∞ ∈ (0.813; 1.13). The cascade flows were suggested in Institute of Thermomechanics by Mr. Dvořák and flows were investigated experimentally. The structure of flow seems to be very complicated. It is possible to observe subsonic and supersonic part, shock wave structure, interaction of shock wave and boundary layer, wake etc. We investigated these flows numerically using composite scheme in the form of finite volume method for governing system of Euler equations. These numerical results are compared to experimental data of IT CAS CZ using comparison of several regimes with increasing upstream Mach numbers. The second problem is an unsteady viscous flow with very low upstream Mach number M∞ ≈ 0.02 in a 2D channel with a moving part of solid wall as a function of time. The flow is described by the system of Navier-Stokes equations for compressible laminar flows. The problem is numerically solved by MacCormack finite volume scheme. Moved grid of quadrilateral cells is considered in the form of conservation laws using Arbitrary Lagrangian-Eulerian method.
Journal of Computational Physics, 2020
The topic of the paper is accuracy analysis of acoustic propagation simulation in low Mach number flows, by finite volume co-located discretisation methods of the time-dependent compressible fluid Euler equations that use the concept of convection-pressure splitting (CPS). These are algorithms that split the flux vectors into a part associated to the convection by the fluid particles, and a part associated to the propagation of the pressure waves. For the convection part, the appropriate space discretisation is the upwind one. For the pressure part, there are alternatives. We discern five types of algorithms that all are adapted for use in low Mach number flows, and thus are considered as all Mach number algorithms. We study the behaviour of the different types for the propagation of small pressure perturbations, of discontinuous or smooth shape, in low Mach number flows. We demonstrate that four of the proposed algorithms of convection-pressure split type are dissipative for such applications, although they are designed for low Mach number flows. The objective of the paper is to analyse why some algorithms are appropriate for acoustic propagation simulation and why some are not appropriate.
2012
ABSTRACT A novel extension to SMAC scheme is proposed for variable density flows under low Mach number approximation. The algorithm is based on a predictor—corrector time integration scheme that employs a projection method for the momentum equation. A constant-coefficient Poisson equation is solved for the pressure following both the predictor and corrector steps to satisfy the continuity equation at each time step.
The low Mach number setting is a singular limiting situation in compressible flows. As Mach number approaches zero, compressible (density-based) flow solvers suffer severe deficiencies, both in efficiency and accuracy. There are two main approaches advocated in the development of algorithms for the computation of low Mach number flows; first, There is the modification of compressible solvers (density-based) downward to low Mach numbers; second, extending incompressible solvers (pressurebased) towards this regime. Here, we present a brief review of the literature in this area. This addresses the modifications necessary to effectively apply density-based schemes and develop compressible pressure-based schemes to such low Mach number configurations.
2004
In the context of the direct numerical simulation of low MACH number reacting flows, the aim of this article is to propose a new approach based on the integration of the original differential algebraic (DAE) system of governing equations, without further differentiation. In order to do so, while preserving a possibility of easy parallelization, it is proposed to use a one-step index 2 DAE time-integrator, the Half Explicit Method (HEM). In this context, we recall why the low MACH number approximation belongs to the class of index 2 DAEs and discuss why the pressure can be associated with the constraint. We then focus on a fourth-order HEM scheme, and provide a formulation that makes its implementation more convenient. Practical details about the consistency of initial conditions are discussed, prior to focusing on the implicit solve involved in the method. The method is then evaluated using the Modified KAPS Problem, since it has some of the features of the low MACH number approximation. Numerical results are presented, confirming the above expectations. A brief summary of ongoing efforts is finally provided. The authors would like to thank E. HAIRER and C.A. KENNEDY for their patience in the face of numerous questions and for their priceless comments. This article also benefi ted greatly of discussions with B. DEBUSSCHERE and G. WANNER.
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