Turbulent axisymmetric near-wake at Mach four with base injection

Przirembel, C. E. G.; Valentine, Daniel T.

doi:10.2514/3.6104

Cited by 18 publications

(2 citation statements)

References 1 publication

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“…In the past couple of decades several numerical studies of supersonic base flow have been performed [4][5][6][7][8][9][10][11][12][13][14][15][16][17], while only a few numerical studies of base bleed [18][19][20][21][22] were performed mostly focused on validating the experimental results obtained by Mathur and Dutton [2][3]. Sahu and Heavy [23] performed RANS (Reynolds Averaged Navier Stokes) simulation with limited success in predicting the distribution of axial velocity component along the centerline.…”

Section: Introductionmentioning

confidence: 99%

Numerical study of flow physics in supersonic base-flow with mass bleed

Das

2016

Aerospace Science and Technology

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Large Eddy Simulation (LES) with dynamic sub-grid scale eddy viscosity model has been applied to numerically investigate the evolution of complicated flow structures in supersonic base flow with mass bleed. Mean flow properties obtained from numerical simulations, such as axial velocity, pressure on the base surface, have been compared with the experimental measurements to show that LES is able to predict the mean flow properties with acceptable accuracy. The data obtained from LES has been further analyzed to understand the evolution of coherent structures in the flow field. Periodical shedding of vortical structures from the outer shear layer has been observed and it has also been found that this vortex shedding is associated with the flapping of the outer shear layer. The frequency of flapping of the outer shear layer has been found out and the phase-averaged streamlines have been analyzed to further study the evolution of vortical structures associated with this flapping. The phase-averaged streamline plots clearly elucidate the evolution of vortical structures along the outer shear layer. Further, the study of these structures is investigated by performing Proper Orthogonal Decomposition (POD) analysis of the data, obtained along the central plane in the wake region. The POD results also 2 seem to agree well with the observations made in the phase averaged streamline plots, as the concentrated energy and enstropy are observed in the outer shear layer with fewer POD modes.

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Section: Introductionmentioning

confidence: 99%

Numerical study of flow physics in supersonic base-flow with mass bleed

Das

2016

Aerospace Science and Technology

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“…Figure 2 shows that injecting small amounts of gas into the flow field behind the base of the projectile will split the originally large recirculation zone into two parts. One recirculation region remains at the symmetry axis and the other one is formed right behind the base corner [4][5][6][7]. As the mass flow rate increases, the recirculation zone at the axis is pushed further out and the other one at the base corner becomes larger.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulations in obtaining drag reduction for projectile with base bleed

Belaidouni¹,

Živković²,

Samardžić³

2016

Sci Tech Rev

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An artillery projectile in flight produces a low pressure area immediately behind the projectile which creates a force called base drag which lessens the velocity of the projectile. It is known that theoretically this base resistance can be reduced or even eliminated by allowing a stream of hot gas to flow out of the base surface of the projectile in a suitable manner. The effect produced by this stream of hot gas is called base-bleed effect. The internal ballistic calculation of existing base bleed configuration is presented in the paper. A numerical simulation of axisymmetric body projectiles was obtained with the Reynolds Averaged Navier-Stokes (RANS) computational fluid dynamics software (CFD). Also, two turbulence models were tested and validated with the semi empirical prediction. The realizable k-ɛ turbulence model was chosen for calculation of aerodynamic drag of the projectile with and without base bleed effect. Computed result show a drag reduction with base bleed of about 12% in supersonic flow regime

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The role of flow visualization in the study of afterbody and base flows

Mueller¹

1985

Experiments in Fluids

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Turbulent axisymmetric near-wake at Mach four with base injection

Cited by 18 publications

References 1 publication

Numerical study of flow physics in supersonic base-flow with mass bleed

Numerical study of flow physics in supersonic base-flow with mass bleed

Numerical simulations in obtaining drag reduction for projectile with base bleed

The role of flow visualization in the study of afterbody and base flows

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