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

Effect of Forward-Facing Steps on Boundary Layer Transition at a Subsonic Mach Number

Costantini, Marco and Risius, Steffen and Klein, Christian and Kühn, Winfried (2016) Effect of Forward-Facing Steps on Boundary Layer Transition at a Subsonic Mach Number. In: New Results in Numerical and Experimental Fluid Mechanics X Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 132. Springer International Publishing. pp. 203-214. ISBN 978-3-319-27278-8. ISSN 1606-2909

[img] PDF - Registered users only
1MB

Official URL: http://www.springer.com/de/book/9783319272788

Abstract

Experiments were conducted at a subsonic Mach number in the Cryogenic Ludwieg-Tube Göttingen to study the influence of surface imperfections on boundary layer transition. Forward-facing steps of different height were installed on two spanwise invariant wind tunnel models and their effect on transition was examined at high chord Reynolds numbers and various streamwise pressure gradients. Transition, detected non-intrusively by means of the Temperature-Sensitive Paint technique, was found to gradually move upstream towards the step location with increasing step Reynolds numbers and relative step height. Larger flow acceleration had a favorable influence on the transition Reynolds number even in the presence of forward-facing steps, but also increased the sensitivity of boundary layer transition to the surface excrescences. The plots of the relative change in transition location as a function of step Reynolds number and relative step height gave good correlations of the results obtained with both wind tunnel models. The correlations were practically independent of the streamwise pressure gradient. Criteria for allowable tolerances on low-sweep Natural Laminar Flow surfaces can now be established from the functional relations determined in this work.

Item URL in elib:https://elib.dlr.de/91216/
Document Type:Contribution to a Collection
Additional Information:Online ISBN: 978-3-642-35680-3, E-ISSN: 1860-0824, DOI: 10.1007/978-3-319-27279-5, Buchuntertitel: Contributions to the 19th STAB/DGLR Symposium Munich, Germany, 2014, Library of Congress Control Number: 2015958857
Title:Effect of Forward-Facing Steps on Boundary Layer Transition at a Subsonic Mach Number
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Costantini, MarcoMarco.Costantini (at) dlr.dehttps://orcid.org/0000-0003-0642-0199
Risius, Steffensteffen.risius (at) dlr.deUNSPECIFIED
Klein, Christianchristian.klein (at) dlr.deUNSPECIFIED
Kühn, WinfriedAirbus Operations SASUNSPECIFIED
Date:January 2016
Journal or Publication Title:New Results in Numerical and Experimental Fluid Mechanics X
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Volume:132
DOI :10.1007/978-3-319-27279-5_18
Page Range:pp. 203-214
Editors:
EditorsEmail
Dillmann, AndreasDLR
Heller, GerdAirbus Deutschland, Bremen, Germany
Wagner, ClausDLR
Krämer, EwaldUni Stuttgart, Germany
Breitsamter, ChristianTU München, Germany
Publisher:Springer International Publishing
Series Name:Notes on Numerical Fluid Mechanics and Multidisciplinary Design
ISSN:1606-2909
ISBN:978-3-319-27278-8
Status:Published
Keywords:Boundary layer transition; forward-facing steps; Temperature-Sensitive Paint, TSP
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 - Simulation and Validation
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Experimental Methods
Deposited By: Costantini, Dr.-Ing. Marco
Deposited On:04 May 2016 16:09
Last Modified:12 Apr 2018 14:30

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.