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Investigation of shock-induced boundary-layer transition in transonic high Reynolds number flows using Temperature-Sensitive Paints

Costantini, Marco and Klein, Christian (2019) Investigation of shock-induced boundary-layer transition in transonic high Reynolds number flows using Temperature-Sensitive Paints. In: 15th International Conference on Fluid Control, Measurements and Visualization (FLUCOME 2019) (214), 1 - 2. University of Naples Federico II. 15th International Conference on Fluid Control, Measurements and Visualization (FLUCOME 2019), 27.-30. Mai 2019, Neapel, Italien.

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Official URL: https://flucome2019.unina.it/e-book/FLUCOME2019.html

Abstract

Shock-wave / boundary-layer interaction (SWBLI) is a complex phenomenon occurring in a variety of flows. On laminar and supercritical wings at transonic flow conditions and chord Reynolds numbers up to approximately 20 million, SWBLI can be involved in the transition process leading the laminar boundary layer to turbulence. At small angles of attack (typically below 1.5°), the laminar boundary layer over the suction side of the wing is accelerated, and therefore stabilized, for a significant portion of the wing chord length. The supersonic flow region is then terminated by a shock that interacts with the boundary layer; in particular, the abrupt pressure increase induces the formation of a laminar separation bubble, and the foot of the shock has a characteristic λ-structure. Transition occurs within the laminar separation bubble and is investigated in the present work by means of the Temperature-Sensitive Paint (TSP) measurement technique. Results of SWBLI in transitional boundary layers, obtained on natural laminar flow and supercritical airfoil models at transonic flow conditions and high Reynolds numbers, will be presented and analyzed in this contribution.

Item URL in elib:https://elib.dlr.de/127748/
Document Type:Conference or Workshop Item (Speech)
Additional Information:Extended abstract ID: 214. FLUCOME2019-214.
Title:Investigation of shock-induced boundary-layer transition in transonic high Reynolds number flows using Temperature-Sensitive Paints
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Costantini, MarcoMarco.Costantini (at) dlr.dehttps://orcid.org/0000-0003-0642-0199
Klein, Christianchristian.klein (at) dlr.dehttps://orcid.org/0000-0001-7592-6922
Date:May 2019
Journal or Publication Title:15th International Conference on Fluid Control, Measurements and Visualization (FLUCOME 2019)
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Page Range:1 - 2
Editors:
EditorsEmail
Cardone, Gennarogcardone@unina.it
Publisher:University of Naples Federico II
Series Name:E-Book Proceedings
Status:Published
Keywords:Shock, Transition, Temperature-sensitive paint, SWBLI
Event Title:15th International Conference on Fluid Control, Measurements and Visualization (FLUCOME 2019)
Event Location:Neapel, Italien
Event Type:international Conference
Event Dates:27.-30. Mai 2019
Organizer:University of Naples Federico II
Institution:Deutsches Zentrum für Luft- und Raumfahrt e.V.
Department:AS-EXV
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
Deposited By: Micknaus, Ilka
Deposited On:25 Jun 2019 15:25
Last Modified:31 Jul 2019 20:25

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