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Application of an Adaptive Shock Control Bump for Drag Reduction on a Variable Camber NLF Wing

Werner, Michael (2018) Application of an Adaptive Shock Control Bump for Drag Reduction on a Variable Camber NLF Wing. In: AIAA SciTech 2018. AIAA SciTech 2018, 08.-13. Jan. 2018, Kissimmee, USA. doi: 10.2514/6.2018-0789.

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Official URL: https://doi.org/10.2514/6.2018-0789


A numerical study concerning the application of a finite pan shock control bump (SCB) on a natural laminar flow (NLF) wing was performed. To assess the potential Performance gain by using a combination of a deployable SCB and variable camber (VC), several parametric studies have been carried out. They were performed on a threedimensional halfmodel of an NLF wing. Results will be presented concerning the effect of shock Position and SCB height on the achievable drag reduction. Additionally, results concerning the effect of VC on drag as well as its application as a means to correctly position the shock with regard to the SCB will be presented. For the given geometry, a maximum drag re- duction of up to 5.6% was achieved. The work presented in this paper was done in the LDAinOP project (Low Drag Aircraft in Operation), as a part of the German national research project LuFoV-1, in cooperation with Airbus and the University of Stuttgart.

Item URL in elib:https://elib.dlr.de/115340/
Document Type:Conference or Workshop Item (Speech)
Title:Application of an Adaptive Shock Control Bump for Drag Reduction on a Variable Camber NLF Wing
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Werner, Michaelmichael.werner (at) dlr.deUNSPECIFIED
Journal or Publication Title:AIAA SciTech 2018
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
DOI :10.2514/6.2018-0789
Keywords:SCB, Flow Control, Drag, Simulation
Event Title:AIAA SciTech 2018
Event Location:Kissimmee, USA
Event Type:international Conference
Event Dates:08.-13. Jan. 2018
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 - Concepts and Integration (old)
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > High Speed Configurations, GO
Deposited By: Werner, Michael
Deposited On:09 Oct 2018 13:59
Last Modified:19 Oct 2018 11:12

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