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The effect of pressure gradient and a non-adiabatic surface on boundary layer transition investigated by means of TSP

Costantini, Marco and Hein, Stefan and Henne, Ulrich and Koch, Stefan and Sachs, Werner and Schojda, Lukas and Rosemann, Henning and Koop, Lars (2013) The effect of pressure gradient and a non-adiabatic surface on boundary layer transition investigated by means of TSP. AIAA. 51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 07. - 10. Jan. 2013, Grapevine (Dallas/Ft. Worth Region), Texas, USA. DOI: 10.2514/6.2013-1137

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Official URL: http://arc.aiaa.org/doi/pdf/10.2514/6.2013-1137

Abstract

The influence of streamwise pressure gradient and a non-adiabatic wing surface on boundary layer transition was experimentally investigated at the DNW-KRG blow-down wind tunnel facility in Göttingen, Germany. Boundary layer transition was detected non-intrusively by means of the Temperature-Sensitive Paint technique. A new wind tunnel model was designed with the aim of systematically investigating the influence of streamwise pressure gradient and a non-adiabatic wing surface, including Reynolds number effects and Mach number effects, on boundary layer transition. The model was tested at high Reynolds numbers and at a high subsonic Mach number. Favorable, neutral, and unfavorable streamwise pressure gradients were considered and various temperature differences between flow and model surface were implemented. More pronounced negative streamwise pressure gradients and surface temperatures closer to the adiabatic wall temperature were shown to stabilize the boundary layer and allowed larger transition Reynolds numbers to be achieved. The resulting effect of the coupling of streamwise pressure gradient and a non-adiabatic wing surface was found to be strongly dependent on the considered stability situation. The favorable effect on boundary layer transition of surface temperatures closer to the adiabatic wall temperature was shown to be more pronounced for stability situations characterized by a markedly negative pressure gradient.

Item URL in elib:https://elib.dlr.de/80727/
Document Type:Conference or Workshop Item (Speech, Paper)
Title:The effect of pressure gradient and a non-adiabatic surface on boundary layer transition investigated by means of TSP
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Costantini, MarcoUNSPECIFIEDUNSPECIFIED
Hein, StefanUNSPECIFIEDUNSPECIFIED
Henne, UlrichUNSPECIFIEDUNSPECIFIED
Koch, StefanUNSPECIFIEDUNSPECIFIED
Sachs, WernerUNSPECIFIEDUNSPECIFIED
Schojda, LukasUNSPECIFIEDUNSPECIFIED
Rosemann, HenningUNSPECIFIEDUNSPECIFIED
Koop, LarsUNSPECIFIEDUNSPECIFIED
Date:2013
Refereed publication:No
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
DOI :10.2514/6.2013-1137
Page Range:pp. 1-24
Publisher:AIAA
Series Name:Conference Proceedings online
Status:Published
Keywords:Laminar-turbulent transition, pressure gradient, non-adiabatic surface, boundary layer, Temperature-Sensitive Paint (PSP)
Event Title:51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
Event Location:Grapevine (Dallas/Ft. Worth Region), Texas, USA
Event Type:international Conference
Event Dates:07. - 10. Jan. 2013
Organizer:The American Institute of Aeronautics and Astronautics (AIAA)
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Simulation & Validation (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Experimental Methods
Institute of Aerodynamics and Flow Technology > High Speed Configurations
Deposited By: Micknaus, Ilka
Deposited On:18 Apr 2013 14:19
Last Modified:12 Feb 2018 11:53

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