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

Statnikov, Vladimir and Saile, Dominik and Meiss, Jan-Hendrik and Henckels, A. and Gülhan, Ali and Schröder, W. (2015) Experimental and numerical investigation of the turbulent wake flow of a generic space launcher configuration. In: Progress in Flight Physics, EUCASS book series - Advances in AeroSpace Sciences pp. 329-350.

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Official URL: https://www.eucass-proceedings.eu/articles/eucass/abs/2015/01/eucass7p329/eucass7p329.html

Abstract

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 flow phenomena of space vehicles at upper stages of the flight trajectory. The experiments are done at Ma∞ = 6 and ReD = 1.7 · 106 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 different 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 effects are minimal compared to an axisymmetric configuration. In the blunt-base case, the turbulent supersonic boundary layer undergoes a strong aftexpansion on the model shoulder leading to the formation of a confined 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 configurations, the pressure fluctuations on the base wall feature dominant frequencies at SrD ≈ 0.05 and SrD ≈ 0.2-0.27, but are of small amplitudes (prms/p∞ = 0.02-0.025) compared to the main body boundary layer. For the nozzle dummy configuration, when moving downstream along the nozzle extension, the wall pressure is increasingly influenced by the reattaching shear layer and the periodic low-frequency behavior becomes less pronounced. Directly behind the reattachment point, the wall pressure reaches maximum mean and root-mean-square (rms) values of about p/p∞ = 1 and p′rms/p∞ = 0.1 and features a broadband specrms trum without distinct frequencies determined by the incoming turbulent supersonic boundary layer.

Item URL in elib:https://elib.dlr.de/126386/
Document Type:Book Section
Title:Experimental and numerical investigation of the turbulent wake flow of a generic space launcher configuration
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Statnikov, VladimirRWTH AachenUNSPECIFIED
Saile, DominikDominik.Saile (at) dlr.deUNSPECIFIED
Meiss, Jan-HendrikRWTH AachenUNSPECIFIED
Henckels, A.DLRUNSPECIFIED
Gülhan, AliAli.Guelhan (at) dlr.deUNSPECIFIED
Schröder, W.RWTH AachenUNSPECIFIED
Date:2015
Journal or Publication Title:Progress in Flight Physics, EUCASS book series - Advances in AeroSpace Sciences
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Volume:7
Page Range:pp. 329-350
Status:Published
Keywords:near-wake flow, jets, flow interaction, hypersonic flight, space transportation systems, experiments, numerics
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 for Aerodynamics and Flow Technology > Supersonoc and Hypersonic Technology
Deposited By: Saile, Dominik
Deposited On:13 Feb 2019 10:10
Last Modified:31 Jul 2019 20:24

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