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Investigations on the turbulent wake of a generic space launcher geometry in the hypersonic flow Regime; Beitrag im Sammelband

Saile, Dominik and Gülhan, Ali and Henckels, Andreas and Glatzer, Christian and Statnikov, Vladimir and Meinke, Matthias (2013) Investigations on the turbulent wake of a generic space launcher geometry in the hypersonic flow Regime; Beitrag im Sammelband. In: Progress in Flight Physics EDP Sciences. pp. 209-234.

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Official URL: https://www.eucass-proceedings.eu/articles/eucass/abs/2013/02/eucass5p209/eucass5p209.html


The turbulent wake flow of generic rocket configurations is investigated experimentally and numerically at a freestream Mach number of 6.0 and a unit Reynolds number of 10 106 m−1. The flow condition is based on the trajectory of Ariane V-like launcher at an altitude of 50 km, which is used as the baseline to address the overarching tasks of wake flows in the hypersonic regime like fluid-structural coupling, reverse hot jets and base heating. Experimental results using pressure transducers and the high-speed Schlieren measurement technique are shown to gain insight into the local pressure fluctuations on the base and the oscillations of the recompression shock. This experimental configuration features a wedgeprofiled strut orthogonally mounted to the main body. Additionally, the influence of cylindrical dummy nozzles attached to the base of the rocket is investigated, which is the link to the numerical investigations. Here, the axisymmetric model possesses a cylindrical sting support of the same diameter as the dummy nozzles. The sting support allows investigations for an undisturbed wake flow. A time-accurate zonal Reynolds-Averaged Navier-Stokes/Large Eddy Simulation (RANS/LES) approach is applied to identify shocks, expansion waves, and the highly unsteady recompression region numerically. Subsequently, experimental and numerical results in the strut-averted region are compared with regard to the wall pressure and recompression shock frequency spectra. For the compared configurations, experimental pressure spectra exhibit dominant Strouhal numbers at about SrD = 0.03 and 0.27, and the recompression shock oscillates at 0.2. In general, the pressure and recompression shock fluctuations numerically calculated agree reasonably with the experimental results. The experiments with a blunt base reveal base-pressure spectra with dominant Strouhal numbers at 0.08 at the center position and 0.145, 0.21-0.22, and 0.31-0.33 at the outskirts of the base.

Item URL in elib:https://elib.dlr.de/114153/
Document Type:Contribution to a Collection
Title:Investigations on the turbulent wake of a generic space launcher geometry in the hypersonic flow Regime; Beitrag im Sammelband
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Journal or Publication Title:Progress in Flight Physics
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Page Range:pp. 209-234
Publisher:EDP Sciences
Keywords:Space Transportation System, Generic Launcher, Wake Flow, Hypersonic, Shock Oscillation, Numerical Simulation, Experiment, LES
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Raumfahrzeugsysteme - Anlagen u. Messtechnik (old)
Location: Köln-Porz
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Deposited By: Saile, Dominik
Deposited On:19 Sep 2017 11:25
Last Modified:31 Jul 2019 20:11

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