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Development of a wind tunnel experiment for vortex dominated flow at a pitching Lambda wing

Wiggen, Stefan and Voß, Guido (2014) Development of a wind tunnel experiment for vortex dominated flow at a pitching Lambda wing. CEAS Aeronautical Journal, pp. 1-10. Springer. DOI: 10.1007/s13272-014-0121-4 ISSN 1869-5582

Full text not available from this repository.

Official URL: http://dx.doi.org/10.1007/s13272-014-0121-4

Abstract

A half wing model, a test rig and new wind tunnel walls were designed to study the vortex development at a lambda wing. The model has a sweep angle of 53° and a round leading edge. It is designed for pitching oscillations around a mean angle of attack of up to 20° up to a free stream Mach number of 0.7. Unsteady aerodynamic load data shall be delivered for aeroelastic simulations of Unmanned Combat Aerial Vehicles. Due to the highly nonlinear aerodynamic character, the design and sizing of the model had to take into account load cases with beginning and fully developed vortices. Furthermore, the different characters at subsonic and transonic speeds had to be included. Coupled simulations with a finite element model including the mounting and the connection to the actuation system were performed to assess the stability and the dynamic response of the model. Furthermore, the test concept and the process of the design of the model will be described.

Item URL in elib:https://elib.dlr.de/90321/
Document Type:Article
Title:Development of a wind tunnel experiment for vortex dominated flow at a pitching Lambda wing
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Wiggen, Stefanstefan.wiggen (at) dlr.deUNSPECIFIED
Voß, Guidoguido.voss (at) dlr.deUNSPECIFIED
Date:2014
Journal or Publication Title:CEAS Aeronautical Journal
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
DOI :10.1007/s13272-014-0121-4
Page Range:pp. 1-10
Publisher:Springer
ISSN:1869-5582
Status:Published
Keywords:vortex, lambda wing, round leading edge, high sweep angle, unsteady experiment
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
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity
Deposited By: Grischke, Birgid
Deposited On:29 Oct 2014 10:33
Last Modified:06 Sep 2019 15:24

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