Investigation of the turbulent wake flow of generic launcher configurations via a zonal RANS/LES method

Statnikov, V.; Meiss, Jan-Hendrik; Meinke, Matthias; Schröder, Wolfgang

doi:10.1007/s12567-013-0045-6

Cited by 11 publications

(14 citation statements)

References 21 publications

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“…Statnikov et al [13] showed that the strength of the recompression shocks and expansion waves directly depends on the de §ection of the shedding shear layer which is determined by the tail geometry and, possibly, other geometrical obstacles, e. g., a strongly aftexpanding jet plume that emanates from the nozzle in real §ight conditions. For the blunt-base and nozzle-dummy con¦gurations, the large expansion angles β e of the shedding shear layer shown in Fig.…”

Section: Spatial Wall Pressure Distributionmentioning

confidence: 99%

“…14b, the pressure §uctuations inside the shed shear layer (region (ii) in Fig. 14a) feature a sharp peak at a distinct dominant frequency of about Sr D = 0.2 that appears due to the vortex shedding at the model shoulder [33] and originally Figure 16 Comparison of the numerical RANS/LES (dashed curves) and experimental (solid curves) pressure spectra on the base wall (extracted from [13]) at ϕ = 180 • and r = 40 mm (t = 1200 · 50D/U∞): 1 ¡ blunt base; and 2 ¡ nozzle dummy is not present in the incoming boundary layer. The latter possesses a broadband spectrum without any distinct dominant frequencies over a wide range of Strouhal numbers, as illustrated by curve 1 in Fig.…”

Section: Analysis Of the Dynamic Wake Flow Behaviormentioning

confidence: 99%

“…Direct numerical simulation is at the present time restricted to small Reynolds numbers and also a small integration domain. In contrast, hybrid approaches like DES [12] and zonal RANS/LES [13] allow time-resolved computation of the dynamic wake §ow at practically relevant Reynolds numbers and were found to be a good compromise between costs and accuracy for time-resolved simultations of the dynamic wake §ow of space launchers.…”

Section: Introductionmentioning

confidence: 99%

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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: Spatial Wall Pressure Distributionmentioning

confidence: 99%

Section: Analysis Of the Dynamic Wake Flow Behaviormentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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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

Self Cite

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“…As shown by Statnikov et al [18][19][20] for both transonic and supersonic cases, numerical results such as computed flow field topology, time-averages and fluctuations of base pressure signals as well as its spectra satisfactorily agree with the experimental data from literature and experimental investigations conducted within TRR 40 [21][22][23]. Using classical spectral analysis and correlation methods, several distinct frequencies were identified indicating a periodic behavior of the base-flow dynamics, e.g., Sr D D 0:1 (shear layer flapping), Sr D D 0:2 (von Kármán vortex shedding) as well as a number of dominant peaks at lower (Sr D 0:05/ and considerably higher frequencies (Sr D 0:7 and Sr D 1) with not fully understood origins.…”

mentioning

confidence: 73%

“…DNS is still restricted to low Reynolds numbers and a small integration domain. In contrast, LES (Meliga et al [16]) and particularly hybrid approaches like DES (Deck and Thorigny [17]) and zonal RANS/LES (Statnikov et al [18]) allow time-resolved computation of the dynamic wake flow field at practically relevant Reynolds-numbers and were found to be a good compromise between costs and accuracy for computation of the wake flow of space launchers.…”

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confidence: 99%

Investigations of Unsteady Transonic and Supersonic Wake Flow of Generic Space Launcher Configurations Using Zonal RANS/LES and Dynamic Mode Decomposition

Statnikov

Sayadi

Meinke

et al. 2014

High Performance Computing in Science and Engineering ‘14

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Dynamic mode decomposition (DMD) is applied to time-resolved results of zonal RANS/LES computations of three different axisymmetric generic space launcher configurations having freestream Mach numbers of 0:7 and 6:0. Two different after-body geometries consisting of an attached sting support mimicking an endless nozzle extension and an attached cylindrical after-expanding nozzle are considered. The distinguishing feature of the investigated configurations is the presence of a separation bubble in the wake region. The dynamics of the bubble and the dominant frequencies are analyzed using DMD. The results are then compared to the findings of spectral analysis and temporal filtering techniques. The transonic case displays distinct peaks in the Fourier transform spectra. We illustrate a close agreement between the frequencies of the DMD modes and the aforementioned peaks. From the shape of the DMD modes, it is deduced that most of the peaks are related to the dynamics of the separation bubble and the corresponding shear layer. The same geometry with higher Mach number shows the existence of two distinct DMD modes of axisymmetric and helical nature, respectively. The presence of the helical mode is illustrated through composite DMD of the cylindrical velocity components. Finally, when considering the free-flight configuration we were able to identify DMD modes with frequency Sr D 1 which results in the flapping motion of the shear layer and a mode of a lower frequency which causes the breathing of the recirculation bubble. Motivation and ObjectivesAlthough in most cases the base geometry of a space launcher is quite simple and can be generically modeled by two coaxial cylinders mimicking the main body and the attached nozzle extension, the wake flow field is determined by different intricate

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Strong Interaction Phenomena

Hirschel¹

2015

Basics of Aerothermodynamics

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Investigation of the turbulent wake flow of generic launcher configurations via a zonal RANS/LES method

Cited by 11 publications

References 21 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

Investigations of Unsteady Transonic and Supersonic Wake Flow of Generic Space Launcher Configurations Using Zonal RANS/LES and Dynamic Mode Decomposition

Strong Interaction Phenomena

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