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

Risius, Steffen and Costantini, Marco and Hein, Stefan and Koch, Stefan and Klein, Christian (2018) Experimental investigation of Mach number and pressure gradient effects on boundary layer transition in two-dimensional flow. In: NOTES ON NUMERICAL FLUID MECHANICS (136), pp. 305-314. Springer International Publishing AG. DOI: 10.1007/978-3-319-64519-3_28 ISBN 978-3-319-64518-6 ISSN 1612-2909

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Official URL: https://link.springer.com/chapter/10.1007/978-3-319-64519-3_28

Abstract

The influence of Mach number (M = 0.35 to 0.65), chord Reynolds number (Rec = 6E6 to 10E6) and pressure gradient (dcp/dx= -0.6 to 0.07 1/m) on laminar-turbulent boundary layer transition was experimentally investigated in the Cryogenic Ludwieg-Tube Göttingen (DNW-KRG). For this investigation the existing two-dimensional wind tunnel model, PaLASTra, which offers a quasi-uniform streamwise pressure gradient, was modified in order to reduce the size of the flow separation at its trailing edge. The streamwise temperature distribution and the location of laminar-turbulent transition were measured by means of temperature-sensitive paint (TSP). It was found that the transition Reynolds number exhibits a linear dependence on the pressure gradient, characterized by the Hartree parameter, and that an increasing Mach number leads to a linear decrease of the transition Reynolds number. This effect is likely due to an increase of the total pressure turbulence level with Mach number in DNW-KRG. The measured pressure and temperature distributions served as input for boundary layer calculations and linear-stability analysis. N-factors were calculated according to compressible and incompressible stability theory. At zero pressure gradient a critical N-factor of approximately 9.5 and 9.0 was found for incompressible and compressible calculations, respectively.

Item URL in elib:https://elib.dlr.de/117952/
Document Type:Conference or Workshop Item (Speech)
Additional Information:E-ISSN: 1860-0824; Online ISBN: 978-3-319-64519-3; https://doi.org/10.1007/978-3-319-64519-3_28; Buchuntertitel: Contributions to the 20th STAB/DGLR Symposium Braunschweig, Germany, 2016
Title:Experimental investigation of Mach number and pressure gradient effects on boundary layer transition in two-dimensional flow
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
Koch, StefanStefan.Koch (at) dlr.deUNSPECIFIED
Klein, ChristianChristian.Klein (at) dlr.deUNSPECIFIED
Date:2018
Journal or Publication Title:NOTES ON NUMERICAL FLUID MECHANICS
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:Yes
DOI :10.1007/978-3-319-64519-3_28
Page Range:pp. 305-314
Editors:
EditorsEmail
Dillmann, AndreasDLR, Göttingen
Heller, GerdAirbus, Bremen
Krämer, EwaldUNI Stuttgart
Wagner, ClausDLR, Göttingen
Bansmer, StephanTU Braunschweig
Radespiel, RolfTU Braunschweig
Semaan, RichardTU Braunschweig
Publisher:Springer International Publishing AG
Series Name:New Results in Numerical and Experimental Fluid Mechanics XI
ISSN:1612-2909
ISBN:978-3-319-64518-6
Status:Published
Keywords:boundary layer transition, COCO, compressibility effect, critical N-factor, Cryogenic Ludwieg-Tube Göttingen (DNW-KRG), freestream pressure fluctuations, laminar-turbulent transition, LILO, linear stability analysis, Mach number effect, PaLASTra, temperature-sensitive paint (TSP), Tollmien-Schlichting waves, transonic wind tunnel
Event Type:Other
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: Bachmann, Barbara
Deposited On:11 Jan 2018 08:47
Last Modified:06 Sep 2018 13:13

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