Numerical simulation of supersonic air flow with transverse hydrogen injection

Lavante, E. von; Zeitz, Dirk; Kallenberg, M.

doi:10.2514/6.1999-4902

Cited by 2 publications

(3 citation statements)

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“…The Reynolds number of such flows is sufficiently large so that a Direct Numerical Simulation (DNS) is currently infeasible. The documented numerical studies of jets in supersonic crossflows relied on Reynolds-Averaged NavierStokes (RANS) equations [5,9,10], Detached Eddy Simulation (DES) [9,10], and Large Eddy Simulation (LES) [11][12][13]. The LES of von Lavante et al [11] uses the Smagorinsky subgrid scale (SGS) model, and includes hydrogen-air chemical reactions with an eightreaction and seven-species model [14].…”

Section: Introductionmentioning

confidence: 99%

“…The documented numerical studies of jets in supersonic crossflows relied on Reynolds-Averaged NavierStokes (RANS) equations [5,9,10], Detached Eddy Simulation (DES) [9,10], and Large Eddy Simulation (LES) [11][12][13]. The LES of von Lavante et al [11] uses the Smagorinsky subgrid scale (SGS) model, and includes hydrogen-air chemical reactions with an eightreaction and seven-species model [14]. In the computations of Fiorina and Lele [12], an artificial nonlinear diffusion term [15,16] is added to the governing flow equations to damp the non-physical oscillations produced around shock waves by the high-order compact scheme.…”

Section: Introductionmentioning

confidence: 99%

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LES of an inclined sonic jet into a turbulent crossflow at Mach 3.6

Ferrante

Matheou

Dimotakis

2011

Journal of Turbulence

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We have performed large-eddy simulation with subgrid scale (LES-SGS) stretchedvortex model of an inclined sonic jet into a supersonic crossflow at Mach 3.6. The main flow features generated by the gas-dynamic interactions of the jet with the supersonic crossflow, such as barrel shock, shear layer, and counter-rotating vortex pair, are numerically captured by the employed LES-SGS. The transition and spatial development of the jet into a supersonic crossflow have been shown to be strongly dependent on the inflow conditions of the crossflow. This result indicates that correct turbulent inflow conditions are necessary to predict the main flow characteristics, dispersion and mixing of a gaseous jet in a supersonic, turbulent crossflow using LES-SGS. This work presents a methodology for the generation of realistic synthetic turbulent inflow conditions for LES of spatially developing, supersonic, turbulent, wall-bounded flows. The methodology is applied to the study of a supersonic turbulent flow over a flat wall interacting with an inclined jet. The effects of inflow conditions on the spatial development of the inclined jet are discussed, and then the results are compared with the available experimental data. Also, the dominant vortical structures generated by the jet/turbulent boundary layer interaction are identified as sheets, tilted tubes and discontinuous rings, and a visualization of their spatiotemporal development is provided. The identified vortical structures are shown to be enveloped by the helium mass-fraction isosurface, thus showing the important role of those structures in the dispersion of a gaseous jet in a supersonic crossflow.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

LES of an inclined sonic jet into a turbulent crossflow at Mach 3.6

Ferrante

Matheou

Dimotakis

2011

Journal of Turbulence

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“…Edwards (1992) states that solving the reacting flow around a hypersonic vehicle in powered flight requires hundreds of hours of computing time on a Cray Y-MP. For a three-dimensional computation of viscous, reactive flow mesh sizes easily exceed a million cells (von Lavante et al, 2001) for solving only a specific, limited problem. Fine meshes are required to properly resolve shock waves and viscous shear layers, severely reducing the allowed time-step, especially in the case of a time-accurate calculation.…”

Section: Introductionmentioning

confidence: 99%

Parallel computation of two‐dimensional laminar inert and chemically reactive multi‐species gas flows

Ess

Allen

2005

International Journal of Numerical Methods for Heat &Amp; Fluid Flow

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Purpose -A computational fluid dynamics code for the calculation of laminar hypersonic multi-species gas flows in chemical non-equilibrium in axisymmetric or two-dimensional configuration on shared and distributed memory parallel computers is presented and validated. The code is designed to work efficiently in combination with an automatic domain decompositioning method developed to facilitate efficient parallel computations of various flow problems. Design/methodology/approach -The baseline implicit numerical method developed is the lower-upper symmetric Gauss-Seidel scheme, which is combined with a sub-iteration scheme to achieve time-accuracy up to third-order. The spatial discretisation is based on Roe's flux-difference splitting and various non-linear flux limiters maintaining total-variation diminishing properties and up to third-order spatial accuracy in continuous regions of flow. The domain subdivision procedure is designed to work for single-and multi-block domains without being constrained by the block boundaries, and an arbitrary number of processors used for the computation. Findings -The code developed reproduces accurately various types of flows, e.g. flow over a flat plate, diffusive mixing and oscillating shock induced combustion around a projectile fired into premixed gas, and demonstrates close to linear scalability within limits of load imbalance.Research limitations/implications -The cases considered are axisymmetric or two-dimensional, and assume laminar flow. An extension to three-dimensional turbulent flows is left for future work. Originality/value -Results of a parallel computation, utilising a newly developed automatic domain subdivision procedure, for oscillating shock-induced combustion around a projectile and various other cases are presented. The influence of entropy correction in Roe's flux-difference splitting algorithm on diffusive mixing of multi-species flows was examined.

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Numerical simulation of supersonic air flow with transverse hydrogen injection

Cited by 2 publications

References 5 publications

LES of an inclined sonic jet into a turbulent crossflow at Mach 3.6

LES of an inclined sonic jet into a turbulent crossflow at Mach 3.6

Parallel computation of two‐dimensional laminar inert and chemically reactive multi‐species gas flows

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