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Experimental Aerodynamic Assessment and Evaluation of an Agile Highly Swept Aircraft Configuration

Huber, Kerstin Claudie and Schütte, Andreas and Rein, Martin and Löser, T. (2016) Experimental Aerodynamic Assessment and Evaluation of an Agile Highly Swept Aircraft Configuration. Deutscher Luft- und Raumfahrtkongress 2015, 2016-09-13 - 2016-09-15, Rostock, Deutschland.

Full text not available from this repository.

Official URL: http://www.dglr.de/publikationen/2015/370004.pdf


Extensive experimental and numerical investigations on a highly swept generic unmanned combat aerial vehicle (UCAV) configuration of lambda type with a variable leading edge contour have been conducted. Within these investigations it was shown that the flow field is dominated by complex vortex systems including vortex-to-vortex and vortex-to-boundary layer interactions. The vortex dominated flow field has a strong nonlinear influence on the aerodynamic behavior of the configuration. Hence, the controllability aspect is demanding and poses a real challenge in the design of this kind of configuration. Especially the dimensioning of the control surfaces for the lateral- and longitudinal stability aspects of tailless configurations of low aspect ratio and high leading edge sweep poses a challenging task, which is not yet solved. The present paper reviews the experimental aspects of the investigations. In order to understand the problem of lacking lateral- and longitudinal stability for these kind of configuration, experiments in the subsonic and transonic flow regime have been conducted for the SACCON configuration, which has a leading edge sweep of 53° in order to assess the control surface effectiveness of conventional trailing edge control devices. These investigations were undertaken as part of the internal DLR projects FaUSST and Mephisto.

Item URL in elib:https://elib.dlr.de/110279/
Document Type:Conference or Workshop Item (Speech)
Title:Experimental Aerodynamic Assessment and Evaluation of an Agile Highly Swept Aircraft Configuration
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Rein, MartinUNSPECIFIEDhttps://orcid.org/0000-0002-2670-2815UNSPECIFIED
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:lambda wing, delta wing, control surfaces, tailless configuration
Event Title:Deutscher Luft- und Raumfahrtkongress 2015
Event Location:Rostock, Deutschland
Event Type:national Conference
Event Start Date:13 September 2016
Event End Date:15 September 2016
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 - Military Technologies (old)
Location: Braunschweig , Göttingen
Institutes and Institutions:German-Dutch Windtunnels
Institute for Aerodynamics and Flow Technology > High Speed Configurations, GO
Institute for Aerodynamics and Flow Technology > Transport Aircraft
Deposited By: Bachmann, Barbara
Deposited On:06 Jan 2017 13:58
Last Modified:21 Jun 2024 08:30

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