Detached-Eddy Simulation With Compressibility Corrections Applied to a Supersonic Axisymmetric Base Flow

Forsythe, James R.; Hoffmann, Klaus A.; Cummings, Russell M.; Squires, Kyle D.

doi:10.1115/1.1517572

Cited by 149 publications

(75 citation statements)

References 45 publications

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“…Numerical investigations of the turbulent wakes range from various RANS model based solutions [5,6] via detached-eddy simulations (DES) [7,8] and LES [9] to direct numerical simulations (DNS) [10,11]. The base §ow and the base pressure, however, have not always been predicted with su©cient accuracy.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of the turbulent wake flow of a generic space launcher configuration

Statnikov

Saile

Meiss

et al. 2015

Progress in Flight Physics – Volume 7

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The turbulent wake of a generic space launcher at cold hypersonic freestream conditions is investigated experimentally and numerically to gain detailed insight into the intricate base §ow phenomena of space vehicles at upper stages of the §ight trajectory. The experiments are done at Ma ∞ = 6 and Re D = 1.7 · 10 6 m −1 by the German Aerospace Center (DLR) and the corresponding computations are performed by the Institute of Aerodynamics Aachen using a zonal Reynolds-averaged Navier Stokes / Large-Eddy Simulation (RANS/LES) approach. Two di¨erent aft-body geometries consisting of a blunt base and an attached cylindrical nozzle dummy are considered. It is found that the wind tunnel model support attached to the upper side of the main body has a nonnegligible impact on the wake along the whole circumference, albeit on the opposite side, the e¨ects are minimal compared to an axisymmetric con¦guration. In the blunt-base case, the turbulent supersonic boundary layer undergoes a strong aftexpansion on the model shoulder leading to the formation of a con¦ned low-pressure (p/p ∞ ≈ 0.2) recirculation region. Adding a nozzle dummy causes the shear layer to reattach on the its wall at x/D ∼ 0.6 and the base pressure level to increase (p/p ∞ ≈ 0.25) compared to the blunt-base case. For both con¦gurations, the pressure §uctuations on the base wall feature dominant frequencies at Sr D ≈ 0.05 and Sr D ≈ 0.2 0.27, but are of small amplitudes (p rms /p ∞ = 0.02 0.025) compared to the main body boundary layer. For the nozzle dummy con¦guration, when moving downstream along the nozzle extension, the wall pressure is increasingly in §uenced by the reattaching shear layer and the periodic low-frequency behavior

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Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of the turbulent wake flow of a generic space launcher configuration

Statnikov

Saile

Meiss

et al. 2015

Progress in Flight Physics – Volume 7

View full text Add to dashboard Cite

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“…For natural applications of DES, RANS is applied in the boundary layer, while outside the boundary layer in the separated region, LES is used. An array of flows ranging from building block applications such as the flow over a cylinder, sphere, aircraft forebody, and missile base to complex geometries including full aircraft have been modeled successfully using DES Travin et al [1999], Squires et al [2001], Constantinescu et al [2002], Forsythe et al [2002], Hansen and Forsythe [2003]. These and other applications illustrate the capability of DES to accurately resolve chaotic unsteady features in the separated regions along with a rational treatment of the attached boundary layers.…”

Section: Numeric Simulationmentioning

confidence: 99%

Flow Control

Fagley¹

2013

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“…[22,23] to match the upstream boundary layer thickness at a distance of 1 mm prior to the base. Figure 8 depicts the construction of the gird, which consists 2.39×10 6 cells and has been proved fine enough to represent the flowfield [24].…”

Section: Supersonic Base Flowmentioning

confidence: 99%

Towards an entropy-based detached-eddy simulation

Zhao

Yan

et al. 2013

Sci. China Phys. Mech. Astron.

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A concept of entropy increment ratio ( s ) is introduced for compressible turbulence simulation through a series of direct numerical simulations (DNS). s represents the dissipation rate per unit mechanical energy with the benefit of independence of freestream Mach numbers. Based on this feature, we construct the shielding function f s to describe the boundary layer region and propose an entropy-based detached-eddy simulation method (SDES). This approach follows the spirit of delayed detached-eddy simulation (DDES) proposed by Spalart et al. in 2005, but it exhibits much better behavior after their performances are compared in the following flows, namely, pure attached flow with thick boundary layer (a supersonic flat-plate flow with high Reynolds number), fully separated flow (the supersonic base flow), and separated-reattached flow (the supersonic cavity-ramp flow). The Reynolds-averaged Navier-Stokes (RANS) resolved region is reliably preserved and the modeled stress depletion (MSD) phenomenon which is inherent in DES and DDES is partly alleviated. Moreover, this new hybrid strategy is simple and general, making it applicable to other models related to the boundary layer predictions. Advances in computer speeds have made it possible to utilize more accurate methods of simulating and modeling turbulent flows. However, grid requirements and time cost typically restrict direct numerical simulation (DNS) and even large eddy simulation (LES) to only low Reynolds numbers. That is, Reynolds-averaged Navier-Stokes (RANS) equations along with a turbulence model seem still to be a powerful tool for engineering aerodynamic analysis nowadays, whereas, traditional RANS approaches do not resolve any turbulent flow structures, but model the effect of turbulence on the mean flow in terms of representative mean turbulence scales. As a result, all spectral effects are lost in the time averaging process. The unsteady variant of this, URANS, although managing to resolve non-stationary mean flows, will produce too much eddy viscosity polluting the predicted fields [1,2]. For many turbulent flows of engineering importance, traditional RANS or URANS modeling may be an awkward approach or may fail to reproduce the relevant flow physics. Hybrid RANS/LES approaches [3] represent a credible alternative improving the description of such flows at a reasonable cost by taking into account most of the flow unsteadiness. The main idea of these methods is to model the turbulent structures in the attached region of the flow and to solve the large length-scale structures elsewhere. One of the most popular RANS/LES methods is the detached-eddy simulation proposed by Spalart et al. in 1997 [4] (termed in the following as DES97), which is based on a modification of the length scale employed by Spalart-Allmaras RANS model (SA) [5]. Since the time it was put forward, DES97 has been applied successfully to numerous engineering flow problems, especially in high-Reynolds number separated

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Detached-Eddy Simulation With Compressibility Corrections Applied to a Supersonic Axisymmetric Base Flow

Cited by 149 publications

References 45 publications

Experimental and numerical investigation of the turbulent wake flow of a generic space launcher configuration

Experimental and numerical investigation of the turbulent wake flow of a generic space launcher configuration

Flow Control

Towards an entropy-based detached-eddy simulation

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