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: 0.88

Impact Factor Rankings

2015 Impact Factor Available summer 2016
2014 Impact Factor 0.875
2013 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

Additional details

5-year impact 0.84
Cited half-life 8.00
Immediacy index 0.00
Eigenfactor 0.00
Article influence 0.37
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

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

  • International Journal of Computational Fluid Dynamics 11/2015; DOI:10.1080/10618562.2015.1112001

  • International Journal of Computational Fluid Dynamics 11/2015; DOI:10.1080/10618562.2015.1111342

  • International Journal of Computational Fluid Dynamics 09/2015; DOI:10.1080/10618562.2015.1081180
  • [Show abstract] [Hide abstract]
    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; 29(3):1-10. DOI:10.1080/10618562.2015.1043735
  • [Show abstract] [Hide abstract]
    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; 29(3):1-15. DOI:10.1080/10618562.2015.1032271
  • [Show abstract] [Hide abstract]
    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; 29(3):1-16. DOI:10.1080/10618562.2015.1028924
  • [Show abstract] [Hide abstract]
    ABSTRACT: This paper presents large eddy simulation (LES) results of incompressible heat and fluid flows around a square cylinder (SC) at zero incident angle at high Reynolds numbers (Re) in the range from 1.25×105 to 3.5×105. LES results are obtained on the basis of swirling strength based sub-grid model, and a higher order upwind scheme developed with respect to the Taylor expansion. It was found that, for the zero incident SC wake flows at a Reynolds number in the range {Re5 = Re/105 ∈ [1.25, 3.5]}, the Strouhal number equals to 0.1079, completely independent of the Reynolds number; the coefficient of drag is around 1.835 with an uncertainty of about 1.9%, almost non-sensitive to the Re. When Re is beyond 3.0×105, the time-averaged peak value of sub-grid viscosity is over 340, implying that the role of sub-grid model is crucial in some regions where vortex motion is active and vortex interaction is intense. The time–spanwise (t-z) averaged sub-grid viscosity ratio profiles and the profiles of fluctuations of the sub-grid viscosity ratio and velocity components at four locations downstream of the SC are presented. The fields of the t-z averaged sub-grid viscosity ratio, and the instantaneous fields of streamwise and spanwise vorticities are also reported and discussed. The predicted mean Nusselt number is compared with empirical correlations, revealing that swirling strength based LES has its potential in predicting natural and industrial flows.
    International Journal of Computational Fluid Dynamics 03/2015; 29(3). DOI:10.1080/10618562.2015.1058373
  • [Show abstract] [Hide abstract]
    ABSTRACT: This paper investigates a very simple method to numerically approximate the solution of the multi-dimensional Riemann problem for gas dynamics, using the literal extension of the Toro Vazquez-Harten Lax Leer (TV-HLL) scheme as its basis. Indeed, the present scheme is obtained by following the Toro–Vazquez splitting, and using the HLL algorithm with modified wave speeds for the pressure system. An essential feature of the TV-HLL scheme is its simplicity and its accuracy in computing multi-dimensional flows. The proposed scheme is carefully designed to simplify its eventual numerical implementation. It has been applied to numerical tests and its performances are demonstrated for some two-dimensional and three-dimensional test problems.
    International Journal of Computational Fluid Dynamics 03/2015; 29(3). DOI:10.1080/10618562.2015.1059933
  • [Show abstract] [Hide abstract]
    ABSTRACT: Localised arc filament plasma actuators are modelled with a validated technique to examine asymmetric control of a perfectly expanded round free jet to deflect its downstream trajectory. The nominal Mach and Reynolds numbers are 1.3 and 1 million, respectively. No-control, symmetrically controlled, and under-expanded jets are also simulated for comparison purposes. Parametric variation of actuation frequency and duty cycle indicate that asymmetric control can alter the trajectory, and, within the confines of the parameters investigated, the optimal forcing scheme was found to correspond to the jet's column-mode frequency and a duty cycle of approximately 60%. Increasing frequency and duty cycle beyond these values have a detrimental effect on control, which is consistent with experimental findings. Asymmetric actuation resulted in significant mixing enhancement on the actuated side, as evidenced by the increased growth rate of the non-dimensional momentum thickness. The effectiveness of control is reduced for under-expanded jet conditions.
    International Journal of Computational Fluid Dynamics 03/2015; 29(3). DOI:10.1080/10618562.2015.1053877
  • [Show abstract] [Hide abstract]
    ABSTRACT: By introducing a mass source/sink term into the continuity equation, the mass-conservation property of the local domain-free discretisation (DFD) method is improved to reduce the spurious oscillations in the simulation of moving-boundary problems. The mass source/sink term is constructed by evaluating the mass flux through the solid part of the control volume split by the immersed boundary. Additionally, some special treatments are given for the multi-valued nodes associated with thin bodies. The introduction of source/sink term has also been extended to three-dimensional problems. Unlike the ghost-cell immersed boundary method, coupling the mass source/sink algorithm with the local DFD method is implemented on triangular and tetrahedral meshes. Compared to the hybrid reconstruction formulation, the properties of the original local DFD method can be preserved better. Numerical experiments for two- and three-dimensional moving-boundary problems show that the present mass source/sink treatment can reduce spurious oscillations effectively.
    International Journal of Computational Fluid Dynamics 03/2015; 29(3). DOI:10.1080/10618562.2015.1058372
  • [Show abstract] [Hide abstract]
    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
  • [Show abstract] [Hide abstract]
    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