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

Pressure Gradient and Nonadiabatic Surface Effects on Boundary Layer Transition

Costantini, Marco and Hein, Stefan and Henne, Ulrich and Klein, Christian and Koch, Stefan and Schojda, Lukas and Ondrus, Vladimir and Schröder, Wolfgang (2016) Pressure Gradient and Nonadiabatic Surface Effects on Boundary Layer Transition. AIAA Journal, 54 (11), pp. 3465-3480. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.J054583. ISSN 0001-1452.

[img] PDF - Only accessible within DLR

Official URL: http://arc.aiaa.org/doi/10.2514/1.J054583


The influence of the streamwise pressure gradient and a nonadiabatic surface on boundary layer transition was experimentally investigated at the Cryogenic Ludwieg-Tube Göttingen, Germany. Boundary layer transition was detected nonintrusively by means of the temperature-sensitive paint technique. The wind-tunnel model was designed to achieve a quasi-uniform streamwise pressure gradient over a large portion of the model chord length. This allowed the effects on boundary layer transition of the streamwise pressure gradient and wall temperature ratio to be decoupled. The model was tested at high Reynolds numbers and at a high subsonic Mach number. Favorable, almostzero, and adverse streamwise pressure gradients were considered; and various temperature differences between the flow and the model surface were implemented. Stronger flow acceleration and lower wall temperature ratios led to an increase of the transition Reynolds number. Larger increases in the transition Reynolds number were obtained at more pronounced flow acceleration for the same reduction in the wall temperature ratio. The measured pressure distributions served as input for boundary layer stability computations, performed according to compressible, linear, local stability theory under the (quasi-) parallel-flow assumption. Amplification factors of the Tollmien–Schlichting waves were shown to be reduced by stronger favorable pressure gradients and lower wall temperature ratios, which was in agreement with the observed variation in the transition Reynolds number.

Item URL in elib:https://elib.dlr.de/81779/
Document Type:Article
Additional Information:Published online: 5 July 2016
Title:Pressure Gradient and Nonadiabatic Surface Effects on Boundary Layer Transition
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Costantini, MarcoMarco.Costantini (at) dlr.dehttps://orcid.org/0000-0003-0642-0199
Hein, Stefanstefan.hein (at) dlr.deUNSPECIFIED
Henne, Ulrichulrich.henne (at) dlr.deUNSPECIFIED
Klein, Christianchristian.klein (at) dlr.deUNSPECIFIED
Koch, StefanStefan.Koch (at) dlr.deUNSPECIFIED
Ondrus, VladimirUni HohenheimUNSPECIFIED
Schröder, WolfgangRWTH AachenUNSPECIFIED
Journal or Publication Title:AIAA Journal
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
DOI :10.2514/1.J054583
Page Range:pp. 3465-3480
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Keywords:Boundary Layer Transition, Temperature-Sensitive Paint, critical pressure coefficient, streamwise pressure gradient
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 (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:21 Oct 2016 14:06
Last Modified:08 Mar 2018 18:42

Repository Staff Only: item control page

Help & Contact
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.