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/ | ||||||||||||||||||
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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: |
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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: |
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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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