elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Numerical and experimental study of nominal 2-D Shock-Wave / Turbulent Boundary Layer Interactions

Touré, Patrice and Schülein, Erich (2018) Numerical and experimental study of nominal 2-D Shock-Wave / Turbulent Boundary Layer Interactions. In: 48th AIAA Fluid Dynamics Conference. AIAA Aviation 2018, 25.-29. Juni 2018, Atlanta, Georgia, USA. DOI: 10.2514/6.2018-3395 ISBN 978-162410553-1

[img] PDF - Registered users only until 1 January 2050
5MB

Official URL: https://arc.aiaa.org/doi/abs/10.2514/6.2018-3395

Abstract

Shock-Wave / Turbulent Boundary Layer Interactions (SWTBLI) play an important role in optimizations of supersonic and hypersonic inlets. For over 60 years SWTBLIs have been experimentally and numerically studied. Recently a scaling approach for the characteristic interaction length has been described for two dimensional attached and separated flows. It resulted in a best fit law for a variety of flow conditions. In this study this approach is used to scale a data set of several nominal two dimensional SWTBLIs at Mach 3. The data set is the outcome of an intensive study with variable impinging shock strengths. Cylindrical shock generators with a variable slenderness ratio are mounted at two alternative positions over a flat plate. Experiments and computational fluid dynamic (CFD) simulations have been conducted. The experiments were carried out in the Ludwieg Tube Facility at DLR G¨ottingen, employing Pitot probe measurements, mean wall pressure measurements and the high-speed shadowgraph technique. The Reynolds-averaged NavierStokes (RANS) simulations have been validated with literature studies and by comparing them to experimental results. The CFD results are used to characterize the flow topology. A method is proposed to automatically detect the interaction lengths from shadowgrams. They were used as input for the abovementioned scaling approach which produced a best fit correlation for this experimental setup. Differences to the best fit law from the literature occur by decreasing the cylinder slenderness accompanied by three dimensional effects influencing the interaction region.

Item URL in elib:https://elib.dlr.de/122612/
Document Type:Conference or Workshop Item (Speech)
Title:Numerical and experimental study of nominal 2-D Shock-Wave / Turbulent Boundary Layer Interactions
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Touré, PatricePatrice.Toure (at) dlr.deUNSPECIFIED
Schülein, ErichErich.Schuelein (at) dlr.dehttps://orcid.org/0000-0002-1125-8504
Date:2018
Journal or Publication Title:48th AIAA Fluid Dynamics Conference
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
DOI :10.2514/6.2018-3395
ISBN:978-162410553-1
Status:Published
Keywords:SWTBLI, SWBLI, supersonic, shock wave
Event Title:AIAA Aviation 2018
Event Location:Atlanta, Georgia, USA
Event Type:international Conference
Event Dates:25.-29. Juni 2018
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > High Speed Configurations, GO
Deposited By: Toure, Patrice
Deposited On:01 Nov 2018 16:18
Last Modified:09 Nov 2018 16:23

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.