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Investigations on the Turbulent Wake of a Generic Space Launcher Geometry in the Hypersonic Flow Regime

Saile, Dominik and Gülhan, Ali and Henckels, Andreas and Glatzer, Christian and Meiß, Jan-Hendrik and Meinke, Matthias and Schröder, Wolfgang (2011) Investigations on the Turbulent Wake of a Generic Space Launcher Geometry in the Hypersonic Flow Regime. In: Proceedings of 4th European Conference for Aerospace Science. EUCASS association. 4th European Conference for Aerospace Science, St. Petersburg, Russia.

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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 x 10^6. The flow condition is based on the trajectory of Ariane V at an altitude of 50 km, which is used as baseline to address the overarching tasks of wake flows in the hypersonic regime like fluid-structural coupling, reverse hot jets and base heating. Experiments using pressure transducers and high-speed schlieren measurement technique were conducted to gain insight into the local pressure fluctuations on the base and the oscillations of the recompression shock. This experimental configuration features a wedge-profiled strut orthogonally mounted to the main body. Additionally, the influence of cylindrical nozzle extensions 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 nozzle extensions. The sting support allows investigations of a undisturbed wake flow. A time-accurate zonal RANS/LES approach was applied to identify shocks, expansion waves, and the highly unsteady recompression region numerically. Subsequently, experimental and numerical results in the strut-averted region are opposed with regard to the wall pressure and recompression shock frequency spectra. For the compared configurations, experimental pressure spectra exhibit dominant Strouhal numbers at about S rD = 0.03 and 0.27 and the recompression shock oscillates at 0.2. In general, the numerical pressure and recompression shock fluctuations agree satisfactorily to 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.

Document Type:Conference or Workshop Item (Speech, Paper)
Title:Investigations on the Turbulent Wake of a Generic Space Launcher Geometry in the Hypersonic Flow Regime
AuthorsInstitution or Email of Authors
Saile, DominikDLR
Gülhan, AliDLR
Henckels, AndreasDLR
Glatzer, ChristianRWTH
Meiß, Jan-HendrikRWTH
Meinke, MatthiasRWTH
Schröder, WolfgangRWTH
Journal or Publication Title:Proceedings of 4th European Conference for Aerospace Science
Refereed publication:No
In ISI Web of Science:No
Publisher:EUCASS association
Keywords:wake, base flow, generic launcher, hypersonic, frequency, pressure fluctuation, schlieren, kulites, high-speed, recompression shock, recirculation region, overexpanded, RANS/LES, zonal, frequency, Strouhal number,
Event Title:4th European Conference for Aerospace Science
Event Location:St. Petersburg, Russia
Event Type:international Conference
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Raumfahrzeugsysteme - Anlagen u. Messtechnik
Location: Köln-Porz
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Deposited By: Dominik Saile
Deposited On:13 Jan 2012 13:39
Last Modified:12 Dec 2013 21:33

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