Reynolds-Averaged Navier-Stokes/Large-Eddy Simulations of Supersonic Base Flow

Simon, Franck; Deck, Sébastien; Guillen, Philippe; Sagaut, Pierre

doi:10.2514/1.21366

Cited by 79 publications

(52 citation statements)

References 42 publications

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“…On the other hand, RANS has completely failed to predict the shear layer expansion in the wake region, possibly because of over estimation of turbulent eddy viscosity leading to high turbulent diffusion of momentum and over prediction of the shear layer growth. While comparing our data with the Simon et al [11], it is noteworthy to mention that the LES modeling as well as mesh count are different in their work and that may have lead to the differences observed in Figs. 5-8.…”

Section: Mean Pressure and Velocity Profilescontrasting

confidence: 46%

“…From Fig. 5, the plot of mean axial velocity along centerline, it can be observed that the current LES study has been able to render a better prediction in the near wake region, though the length of the recirculation region has been slightly over predicted in comparison with the LES study performed by Simon et al [11]. On the other hand, standard k-epsilon model completely fails to predict the length and location of the recirculation region.…”

Section: Mean Pressure and Velocity Profilesmentioning

confidence: 67%

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Numerical investigation of flow structures around a cylindrical afterbody under supersonic condition

Das

2015

Aerospace Science and Technology

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Large Eddy Simulation (LES) with dynamic Smagorinsky model has been applied to numerically investigate the complicated flow structures that evolve in the near wake of a cylindrical after body aligned with a uniform Mach 2.46 flow. Mean flow field properties obtained from numerical simulations, such as axial velocity, pressure on base surface, have been compared with the experimental measurements as well as with other published results. It has been found that standard k-epsilon model fails to predict the flow properties in the recirculation region where better agreement has been observed between the data obtained from LES and experimental measurements. Flow Statistics like turbulent kinetic energy and primary Reynolds' stress have also been calculated and compared with the results obtained from experiments in order to quantitatively assess the ability of LES technique to predict the turbulence properties of flow field in the highly compressible shear layer region. The data obtained from LES has been further analyzed to understand the evolution of coherent structures in the flow field. Proper Orthogonal Decomposition (POD) of the data obtained from central plane in the wake region has been performed in order to reveal the most energetic structures present in the flow field.

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Section: Mean Pressure and Velocity Profilescontrasting

confidence: 46%

Section: Mean Pressure and Velocity Profilesmentioning

confidence: 67%

Numerical investigation of flow structures around a cylindrical afterbody under supersonic condition

Das

2015

Aerospace Science and Technology

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“…Especially within ZDES, there is no need to switch off the subgrid-scale model to simulate accurately jet flows conversely to zonal RANS/implicit large eddy simulation (ILES), which have also proven to be efficient in certain situations like jet flows [39][40][41] and base flows [42][43][44]. The interaction of these instabilities with the pylon is captured by the simulation.…”

Section: (B) Cruise Conditionsmentioning

confidence: 99%

High-fidelity simulations of unsteady civil aircraft aerodynamics: stakes and perspectives. Application of zonal detached eddy simulation

Deck

Gand

Brunet

et al. 2014

Phil. Trans. R. Soc. A.

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This paper provides an up-to-date survey of the use of zonal detached eddy simulations (ZDES) for unsteady civil aircraft applications as a reflection on the stakes and perspectives of the use of hybrid methods in the framework of industrial aerodynamics. The issue of zonal or non-zonal treatment of turbulent flows for engineering applications is discussed. The ZDES method used in this article and based on a fluid problem-dependent zonalization is briefly presented. Some recent landmark achievements for conditions all over the flight envelope are presented, including low-speed (aeroacoustics of high-lift devices and landing gear), cruising (engine-airframe interactions), propulsive jets and off-design (transonic buffet and dive manoeuvres) applications. The implications of such results and remaining challenges in a more global framework are further discussed.

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“…The majority of such studies have primarily made use of laser Doppler velocimetry ͑LDV͒, with the statistical data being used by the computational community to help validate the most promising computational codes, which have typically made use of both Reynolds-averaged Navier-Stokes ͑RANS͒ and large eddy simulation ͑LES͒ techniques. [11][12][13] Of particular interest in recent years has been the study of the instantaneous flow organization of the near wake region. This has been motivated by the recognized importance of the unsteady motion of the reattachment point and the associated recompression shock wave system, which can lead to fluctuating base pressures, 14 as well as fluctuating loads on the body itself.…”

Section: Introductionmentioning

confidence: 99%

Unsteady flow organization of compressible planar base flows

2007

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The unsteady flow features of a series of two-dimensional, planar base flows are examined, within a range of low-supersonic Mach numbers in order to gain a better understanding of the effects of compressibility on the organized global dynamics. Particle image velocimetry is used as the primary diagnostic tool in order to characterize the instantaneous near wake behavior, in combination with data processing using proper orthogonal decomposition. The results show that the mean flowfields are simplified representations of the instantaneous flow organizations. Generally, each test case can be characterized by a predominant global mode, which undergoes an evolution with compressibility, within the Mach number range considered. ͑The term "global mode" is defined herein as an organized global dynamical behavior of the near wake region, recognizing that the near wake dynamics may be describable in terms of several global modes.͒ At Mach 1.46, the predominant global mode can be characterized by a sinuous or flapping motion. With increasing compressibility, this flapping mode decreases, and the predominant global mode evolves into a pulsating motion aligned with the wake axis at Mach 2.27. These global modes play an important role in the distributed nature of the turbulence properties. The turbulent mixing processes become increasingly confined to a narrower redeveloping wake with increasing compressibility. Global maximum levels of the streamwise turbulence intensity and the kinematic Reynolds shear stress occur within the vicinity of the mean reattachment location, and show no systematic trend with compressibility. In contrast, the global maximum level of the vertical turbulence intensity moves upstream from the redeveloping wake toward the mean reattachment location. The vertical turbulence intensity decays thereafter more slowly than the other turbulence quantities. Overall, the local maximum levels of the turbulence properties decrease appreciably with increasing compressibility.

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Reynolds-Averaged Navier-Stokes/Large-Eddy Simulations of Supersonic Base Flow

Cited by 79 publications

References 42 publications

Numerical investigation of flow structures around a cylindrical afterbody under supersonic condition

Numerical investigation of flow structures around a cylindrical afterbody under supersonic condition

High-fidelity simulations of unsteady civil aircraft aerodynamics: stakes and perspectives. Application of zonal detached eddy simulation

Unsteady flow organization of compressible planar base flows

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