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Numerical and Experimental Validation of Three-Dimensional Shock Control Bumps

König, Benedikt and Pätzold, Martin and Lutz, Thorsten and Krämer, Ewald and Rosemann, Henning and Richter, Kai and Uhlemann, Heiko (2009) Numerical and Experimental Validation of Three-Dimensional Shock Control Bumps. Journal of Aircraft, 46 (2), pp. 675-682. American Institute of Aeronautics and Astronautics (AIAA).

Full text not available from this repository.

Abstract

Numerical and experimental studies have been performed to show the potential for drag reductions of an array of discrete three-dimensional shock control bumps. The bump contour investigated was specifically designed by means of CFD-based numerical optimization for wind tunnel testing on a modern transonic airfoil. The experimental investigations focused on turbulent flow at a Reynolds number of 5 million and were carried out at the Transonic Wind Tunnel G¨ottingen. Drag reductions of around 10% in the drag-rise region were found in the experiment even though the results were influenced by wind tunnel interference effects. A detailed numerical study of the wind tunnel environment reproduced the influence of the wind tunnel walls on the bump performance and gave good agreement to the experimental results.

Item URL in elib:https://elib.dlr.de/59320/
Document Type:Article
Title:Numerical and Experimental Validation of Three-Dimensional Shock Control Bumps
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
König, BenediktUniversität StuttgartUNSPECIFIED
Pätzold, MartinUniversität StuttgartUNSPECIFIED
Lutz, ThorstenUniversität StuttgartUNSPECIFIED
Krämer, EwaldUniversität StuttgartUNSPECIFIED
Rosemann, HenningUNSPECIFIEDUNSPECIFIED
Richter, KaiUNSPECIFIEDUNSPECIFIED
Uhlemann, HeikoDNWUNSPECIFIED
Date:1 March 2009
Journal or Publication Title:Journal of Aircraft
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:46
Page Range:pp. 675-682
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Status:Published
Keywords:shock control bump, transonic flow, FLOWer, DNW-TWG
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 - Flight Physics (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > High Speed Configurations
Deposited By: Richter, Kai
Deposited On:06 Jul 2009 14:25
Last Modified:08 Mar 2018 18:40

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