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

Experimental investigation of Mach number and pressure gradient effects on two-dimensional laminar-turbulent boundary layer transition

Risius, Steffen and Costantini, Marco and Hein, Stefan and Klein, Christian and Koch, Stefan (2018) Experimental investigation of Mach number and pressure gradient effects on two-dimensional laminar-turbulent boundary layer transition. In: 20th STAB/DGLR Symposium on New Results in Numerical and Experimental Fluid Mechanics, pp. 80-81. Springer Nature. 20. DGLR-Fachsymposium der STAB, 08.-09. Nov. 2016, Braunschweig, Deutschland. DOI: 10.1007/s00348-018-2538-8 ISBN 978-331964518-6 ISSN 1612-2909

Full text not available from this repository.

Official URL: https://link.springer.com/article/10.1007/s00348-018-2538-8

Abstract

Drag reduction by means of Natural Laminar Flow technology is a promising way to reduce wall shear stress, which can significantly reduce fuel consumption of commercial aircraft. Tollmien-Schlichting (T-S) waves are the dominating mechanism to inducing 'natural' transition in low free-stream disturbance environments for boundary layers developing on 'smooth' two-dimensional surfaces. At these conditions the linear stability theory, in particular the e^N-method, predicts a stabilizing effect of compressibility with an increase in Mach number. However, there is no experimental verification of this effect for Mach numbers up to transonic conditions. In this work we show experimental evidence that may contradict a stabilizing effect of compressibility. A systematic investigation of pressure gradients (dcp/dx = -1.2 – 0.25 1/m), Mach numbers (Ma = 0.35 – 0.77) and chord Reynolds numbers (Rec = 3.5 – 16.0 million, with c = 0.2 m) will be presented.

Item URL in elib:https://elib.dlr.de/104851/
Document Type:Conference or Workshop Item (Speech)
Title:Experimental investigation of Mach number and pressure gradient effects on two-dimensional laminar-turbulent boundary layer transition
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Risius, Steffensteffen.risius (at) dlr.dehttps://orcid.org/0000-0002-5530-9609
Costantini, MarcoMarco.Costantini (at) dlr.dehttps://orcid.org/0000-0003-0642-0199
Hein, Stefanstefan.hein (at) dlr.deUNSPECIFIED
Klein, Christianchristian.klein (at) dlr.deUNSPECIFIED
Koch, StefanStefan.Koch (at) dlr.deUNSPECIFIED
Date:2018
Journal or Publication Title:20th STAB/DGLR Symposium on New Results in Numerical and Experimental Fluid Mechanics
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
DOI :10.1007/s00348-018-2538-8
Page Range:pp. 80-81
Publisher:Springer Nature
Series Name:Notes on Numerical Fluid Mechanics and Multidisciplinary Design
ISSN:1612-2909
ISBN:978-331964518-6
Status:Published
Keywords:Boundary layer Transition, Mach number effect, compressibility, Temperature-Sensitive Paint (TSP)
Event Title:20. DGLR-Fachsymposium der STAB
Event Location:Braunschweig, Deutschland
Event Type:national Conference
Event Dates:08.-09. Nov. 2016
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 for Aerodynamics and Flow Technology > Experimental Methods, GO
Institute for Aerodynamics and Flow Technology > High Speed Configurations, GO
Deposited By: Micknaus, Ilka
Deposited On:16 Dec 2016 12:31
Last Modified:22 Nov 2018 12:45

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.