International Journal of Computational Fluid Dynamics Impact Factor & Information

Publisher: Taylor & Francis

Journal description

The aim of the International Journal of Computational Fluid Dynamics is a continuous and timely dissemination of new and innovative CFD research and developments. The journal is a truly interdisciplinary forum for CFD, and publishes refereed papers on the latest advances in numerical methods in fluid dynamics and their applications to the aeronautrics, hydrodynamics, environmental, and power and process fields. The journal has a distinctive and balanced international contribution, with emphasis on papers dealing with efficient methods to produce accurate predictive numerical tools for flow analysis and design, and those promoting the understanding of the physics of fluid motion. Relevant and innovative practical and industrial applications, as well as those of an interdisciplinary nature, are strongly encouraged.

Current impact factor: 0.72

Impact Factor Rankings

2015 Impact Factor Available summer 2015
2013 / 2014 Impact Factor 0.716
2012 Impact Factor 0.87
2011 Impact Factor 0.943
2010 Impact Factor 0.704
2009 Impact Factor 0.571
2008 Impact Factor 0.43
2007 Impact Factor 0.314
2006 Impact Factor 0.383
2005 Impact Factor 0.434
2004 Impact Factor 0.485
2003 Impact Factor 0.373
2002 Impact Factor 0.238
2001 Impact Factor 0.354
2000 Impact Factor 0.299
1999 Impact Factor 0.271
1998 Impact Factor 0.274
1997 Impact Factor 0.222

Impact factor over time

Impact factor
Year

Additional details

5-year impact 0.92
Cited half-life 6.50
Immediacy index 0.10
Eigenfactor 0.00
Article influence 0.36
Website International Journal of Computational Fluid Dynamics website
Other titles International journal of computational fluid dynamics (Online), Computational fluid dynamics
ISSN 1061-8562
OCLC 49941636
Material type Document, Periodical, Internet resource
Document type Internet Resource, Computer File, Journal / Magazine / Newspaper

Publisher details

Taylor & Francis

  • Pre-print
    • Author can archive a pre-print version
  • Post-print
    • Author can archive a post-print version
  • Conditions
    • Some individual journals may have policies prohibiting pre-print archiving
    • On author's personal website or departmental website immediately
    • On institutional repository or subject-based repository after either 12 months embargo
    • Publisher's version/PDF cannot be used
    • On a non-profit server
    • Published source must be acknowledged
    • Must link to publisher version
    • Set statements to accompany deposits (see policy)
    • The publisher will deposit in on behalf of authors to a designated institutional repository including PubMed Central, where a deposit agreement exists with the repository
    • STM: Science, Technology and Medicine
    • Publisher last contacted on 25/03/2014
    • This policy is an exception to the default policies of 'Taylor & Francis'
  • Classification
    ​ green

Publications in this journal

  • [Show abstract] [Hide abstract]
    ABSTRACT: The diagonally implicit harmonic balance method is developed in an overset mesh topology and applied to unsteady rotor flows analysis. Its efficiency is by reducing the complexity of a fully implicit harmonic balance method which becomes more flexible in handling the higher harmonics of the flow solutions. Applied to the overset mesh topology, the efficiency of the method becomes greater by reducing the number of solution interpolations required during the entire solution procedure as the method reduces the unsteady computation into periodic steady state. To verify the accuracy and efficiency of the method, both hovering and unsteady forward flight of Caradonna and Tung and AH-1G rotors are solved. Compared with wind-tunnel experiments, the numerical results demonstrate good agreements at computational cost an order of magnitude more efficient than the conventional time-accurate computation method. The proposed method has great potential in other engineering applications, including flapping wing vehicles, turbo-machinery, wind-turbines, etc.
    International Journal of Computational Fluid Dynamics 12/2015; 29(1). DOI:10.1080/10618562.2015.1015525
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    ABSTRACT: Particle methods have been seldom verified by a Karman vortex simulation, which is commonly performed as a typical benchmark in computational fluid dynamics. This is mainly due to a difficulty in suppression of occurrence of unphysical voids manifested usually in a strong vortex on account of definition of free surface by the Lagrangian tracking framework with inconsistency in volume conservation. This paper presents a simple and effective scheme as a free-surface boundary condition of projection-based particle methods, namely the MPS (moving particle semi-implicit) and Incompressible SPH (ISPH) methods to handle the free surface with consistency in volume conservation. The new scheme is introduced into the Poisson pressure equation (PPE) with consideration of a potential in void space as space potential particle (SPP), to reproduce physical motions of particles around free surface through a particle–void interaction. The enhancing effect of the newly proposed SPP scheme is shown by simulating a few numerical tests, including a whirling water flow, a two-phase surfacing flow, and a set of Karman vortex simulations.
    International Journal of Computational Fluid Dynamics 12/2015; 29(1). DOI:10.1080/10618562.2015.1006130
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    ABSTRACT: In this paper, a kind of arbitrary high order derivatives (ADER) scheme based on the generalised Riemann problem is proposed to simulate multi-material flows by a coupling ghost fluid method. The states at cell interfaces are reconstructed by interpolating polynomials which are piece-wise smooth functions. The states are treated as the equivalent of the left and right states of the Riemann problem. The contact solvers are extrapolated in the vicinity of contact points to facilitate ghost fluids. The numerical method is applied to compressible flows with sharp discontinuities, such as the collision of two fluids of different physical states and gas-liquid two-phase flows. The numerical results demonstrate that unexpected physical oscillations through the contact discontinuities can be prevented effectively and the sharp interface can be captured efficiently.
    International Journal of Computational Fluid Dynamics 05/2015; DOI:10.1080/10618562.2015.1043735
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    ABSTRACT: Large-eddy simulations (LES) are employed to understand the flow field over a NACA 0015 airfoil controlled by a dielectric barrier discharge (DBD) plasma actuator. The Suzen body force model is utilised to introduce the effect of the DBD plasma actuator. The Reynolds number is fixed at 63,000. Transient processes arising due to non-dimensional excitation frequencies of one and six are discussed. The time required to establish flow authority is between four and six characteristic times, independent of the excitation frequency. If the separation is suppressed, the initial flow conditions do not affect the quasi-steady state, and the lift coefficient of the higher frequency case converges very quickly. The transient states can be categorised into following three stages: (1) the lift and drag decreasing stage, (2) the lift recovery stage, and (3) the lift and drag converging stage. The development of vortices and their influence on control is delineated. The simulations show that in the initial transient state, separation of flow suppression is closely related to the development spanwise vortices while during the later, quasi-steady state, three-dimensional vortices become more important.
    International Journal of Computational Fluid Dynamics 05/2015; DOI:10.1080/10618562.2015.1032271
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    ABSTRACT: Wall boundary modelling is one of the key factors that affect the accuracy of the moving particle semi-implicit (MPS) method. In most implementations of the MPS method, wall boundaries are modelled by discrete wall particles and corresponding phantom particles. In this work, a systematic analysis is performed to demonstrate that the discretised representation of wall boundaries can numerically cause unphysical ‘frictional force’ and ‘bouncing movement’ to nearby fluid particles. This can significantly influence the accuracy of the MPS method. To address these issues, a new fluid-wall interaction model is proposed which replaces the discrete wall particles with a continuous, smooth mathematical description of the particle number density. With the new fluid-wall interaction model, solid boundaries are modelled to retain their physical shapes. Numerical examples demonstrate that the new method generates more accurate and physical results than the original MPS method. In addition to the improved results, the new method also features reduced complexity of MPS modelling and more efficient computation. The method is also envisioned to be applicable to problems with arbitrarily shaped boundaries.
    International Journal of Computational Fluid Dynamics 04/2015; DOI:10.1080/10618562.2015.1028924
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    ABSTRACT: Experimental evidence suggests that short-pulse dielectric barrier discharge actuators are effective for speeds corresponding to take-off and approach of large aircraft, and thus are a fruitful direction for flow control technology development. Large-eddy simulations have reproduced some of the main fluid dynamic effects. The plasma models used in such simulations are semi-empirical, however, and need to be tuned for each flowfield under consideration. In this paper, the discharge physics is examined in more detail with multi-fluid modelling, comparing a five-moment model (continuity, momentum, and energy equations) to a two-moment model (continuity and energy equations). A steady-state, one-dimensional discharge was considered first, and the five-moment model was found to predict significantly lower ionisation rates and number densities than the two-moment model. A two-dimensional, transient discharge problem with an elliptical cathode was studied next. Relative to the two-moment model, the five-moment model predicted a slower response to the activation of the cathode, and lower electron velocities and temperatures as the simulation approached steady-state. The primary reason for the differences in the predictions of the two models can be attributed to the effects of particle inertia, particularly electron inertia in the cathode layer. The computational cost of the five-moment model is only about twice that of the simpler variant, suggesting that it may be feasible to use the more sophisticated model in practical calculations for flow control actuator design.
    International Journal of Computational Fluid Dynamics 03/2015; 29(2):1-12. DOI:10.1080/10618562.2015.1021694
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    ABSTRACT: In this work, we present a fast and parallel finite volume scheme on unstructured meshes applied to complex fluid flow. The mathematical model is based on a three-dimensional compressible low Mach two-phase flows model, combined with a linearised ‘artificial pressure’ law. This hyperbolic system of conservation laws allows an explicit scheme, improved by a block-based adaptive mesh refinement scheme. Following a previous one-dimensional work, the useful numerical density of entropy production is used as mesh refinement criterion. Moreover, the computational time is preserved using a local time-stepping method. Finally, we show through several test cases the efficiency of the present scheme on two- and three-dimensional dam-break problems over an obstacle.
    International Journal of Computational Fluid Dynamics 02/2015; 29(1):1-15. DOI:10.1080/10618562.2015.1012161
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    ABSTRACT: The carbuncle phenomenon normally occurs numerically in the prediction of shock waves in flow computation. Most efforts to remedy this problem concern numerical treatment of the bow shock wave while many evidences declare that the carbuncle phenomenon problem may be unsolvable. This paper studies the numerical instability of the AUSM+ scheme on two-dimensional structured triangular grids. By examining several test cases, it is found that the scheme cannot satisfy robustness against shock-induced anomalies. A more stable version of the AUSM+ scheme (so-called AUSM+δ scheme) is developed by applying the multidimensional dissipation technique to the numerical dissipation term in order to alleviate the shock instability. The dissipation mechanism against perturbations is investigated by applying a linearised discrete analysis to the odd--even decoupling problem. The recursive equations show that the AUSM+δ scheme is less sensitive to such anomalies than the original scheme. Finally, the scheme is further extended to achieve the second-order solution accuracy and evaluated by solving several test cases.
    International Journal of Computational Fluid Dynamics 02/2015; 29(1):1-11. DOI:10.1080/10618562.2015.1010525
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    ABSTRACT: Direct numerical simulations are carried out to explore the use of flow control that delays transition generated by excrescence on a plate-like geometry in subsonic flow. Both forward-facing and rearward-facing steps of small roughness heights are considered in the investigation. These are representative of joints and other surface imperfections on wing sections that disrupt laminar flow, thereby increasing skin friction and configuration drag. Unlike previous studies, the steps have a finite lateral extent, such that sharp edges occur in both the spanwise and streamwise directions, and provide a more realistic characterisation of misaligned panels in aerodynamic configurations. The effect of spanwise corners upon transition is examined, and dielectric barrier discharge plasma-based flow control is applied to delay transition and increase the extent of the laminar flow region. Solutions are obtained to the Navier– Stokes equations that were augmented by source terms used to represent body forces imparted by plasma actuators on the fluid. A simple phenomenological model provided these forces resulting from the electric field generated by the plasma. The numerical method is based upon a high-fidelity scheme and an implicit time-marching approach, on an overset mesh system that is used to represent the finite-span steps. Very small-amplitude numerical forcing is employed to generate perturbations, which are amplified by the geometric disturbances and result in transition, similar to the physical situation. Both continuous and pulsed operations of actuators are considered, and the effectiveness of the control is quantified. Transition with the forward-facing step is considerably exacerbated by the presence of a spanwise edge. Plasma control is minimally effective, even with the use of multiple actuators and increased applied force. For the rearward-facing step, transition is substantially delayed by plasma control with small force application.
    International Journal of Computational Fluid Dynamics 02/2015; 29(2). DOI:10.1080/10618562.2015.1025766
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    ABSTRACT: In this paper, a new computational method is developed based on computational fluid dynamics (CFD) coupled with rigid body dynamics (RBD) and flight control law in an in-house programmed source code. The CFD solver is established based on momentum source method, preconditioning method, lower–upper symmetric Gauss–Seidel iteration method, and moving overset grid method. Two-equation shear–stress transport k − ω turbulence model is employed to close the governing equations. Third-order Adams prediction-correction method is used to couple CFD and RBD in the inner iteration. The wing-rock motion of the delta wing is simulated to validate the capability of the computational method for virtual flight simulation. Finally, the developed computational method is employed to simulate the longitudinal virtual flight of a dual rotor micro air vehicle (MAV). Results show that the computational method can simulate the virtual flight of the dual rotor MAV.
    International Journal of Computational Fluid Dynamics 02/2015; 29(2). DOI:10.1080/10618562.2015.1016426
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    ABSTRACT: In this work, we investigate the dynamics of the near wake in a turbulent flow going past a circular cylinder with/without particles at a moderate Reynolds number using a direct numerical simulation method. High-order finite-deference schemes are applied to solve for the bulk fluid properties, and a Lagrangian approach is adopted to track the individual particles. The single-phase flow is analysed and validated using previous experimental data. Two converged states, U- and V-shaped, are observed in the near wake, which are consistent with the experimental results. For the two-phase flow, the addition of smaller particles shortens the length of the recirculation region and causes a V-shaped profile to form behind the circular cylinder. Furthermore, the particles increase the drag force from the circular cylinder and suppress the vortex shedding frequency. An increase in the turbulent statistics in the very near wake and a decrease in the turbulent statistics further downstream are also observed.
    International Journal of Computational Fluid Dynamics 02/2015; 29(2). DOI:10.1080/10618562.2015.1021693
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    ABSTRACT: Compressible direct numerical simulation (DNS) with a preconditioning method is conducted for the turbulent channel flow of Ret=180 at an extremely low Mach number of 0.005. The turbulence statistics are in excellent agreement with incompressible DNS results, which indicates that the preconditioning method is able to accurately simulate the turbulence at an extremely low Mach number under the condition of sufficient resolution without any subgrid scale model or special treatment of numerical dissipation. In addition, the effects of the computational time step are investigated. It is shown that when the time step is shorter than 0.32 wall units, accurate results can be obtained and the total computational time is independent of the length of the time step. This study thus validates the feasibility of the compressible DNS with a preconditioning method for an extremely low Mach number and provides useful guidelines for simulating turbulence.
    International Journal of Computational Fluid Dynamics 08/2014; DOI:10.1080/10618562.2014.959000
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    ABSTRACT: The present study investigates the electromagnetic braking of buoyancy convective flows occurring in differentially heated cavities, filled with low Prandtl, dilute, incompressible and electrically conducting alloys, and subjected to a constant horizontal temperature gradient. In practice, such flows known as ‘Hadley circulation’ are relevant in material processing technologies, such as the horizontal Bridgman configuration. A collocation spectral numerical method is developed to solve the two-dimensional Navier–Stokes equations, modelling the flow phenomena occurring in such configurations, using a vorticity–stream function formulation. The two components of the velocity are deduced from the stream function and the temperature distribution is obtained through the resolution of the energy conservation equation. The results in terms of velocity and temperature distributions for a given Grashof number are obtained for various Hartmann numbers and show that as the Hartmann number increases, the electromagnetic braking of the flow is observed. Moreover, the results illustrate the changes affecting the flow structure which becomes quasi-parallel in the core region of the cavity for sufficiently high values of Ha and the onset of the Hartmann and parallel layers along the boundaries. Also, with increasing Ha, the isotherms are less affected by the convective flow and become parallel to the vertical walls indicating that heat transfer is mainly achieved by conduction.
    International Journal of Computational Fluid Dynamics 07/2014;
  • [Show abstract] [Hide abstract]
    ABSTRACT: The present study investigates the electromagnetic braking of buoyancy convective flows occurring in differentially heated cavities, filled with low Prandtl, dilute, incompressible and electrically conducting alloys, and subjected to a constant horizontal temperature gradient. In practice, such flows known as ‘Hadley circulation’ are relevant in material processing technologies, such as the horizontal Bridgman configuration. A collocation spectral numerical method is developed to solve the two-dimensional Navier–Stokes equations, modelling the flow phenomena occurring in such configurations, using a vorticity–stream function formulation. The two components of the velocity are deduced from the stream function and the temperature distribution is obtained through the resolution of the energy conservation equation. The results in terms of velocity and temperature distributions for a given Grashof number are obtained for various Hartmann numbers and show that as the Hartmann number increases, the electromagnetic braking of the flow is observed. Moreover, the results illustrate the changes affecting the flow structure which becomes quasi-parallel in the core region of the cavity for sufficiently high values of Ha and the onset of the Hartmann and parallel layers along the boundaries. Also, with increasing Ha, the isotherms are less affected by the convective flow and become parallel to the vertical walls indicating that heat transfer is mainly achieved by conduction.
    International Journal of Computational Fluid Dynamics 07/2014; 28. DOI:10.1080/10618562.2014.936316