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Vortical flow prediction for the design of a wind tunnel experiment with a pitching lambda wing

Wiggen, Stefan and Voß, Guido (2014) Vortical flow prediction for the design of a wind tunnel experiment with a pitching lambda wing. CEAS Aeronautical Journal, pp. 1-13. Springer. DOI: 10.1007/s13272-014-0120-5 ISSN 1869-5582

Full text not available from this repository.

Official URL: http://dx.doi.org/10.1007/s13272-014-0120-5

Abstract

The IWEX wind tunnel model (Instationäres Wirbelexperiment, German for: Unsteady Vortex Experiment) was developed to study vortical flow at static and oscillating angles of attack. Numerical computations were performed beforehand to study important aerodynamic aspects. The focus of this paper is on those results that were affecting the design of the model. The experimental concept of a new test rig, wind tunnel walls and the new half wing model is briefly described. The lambda wing has a purely round leading edge with a constant nose radius to chord ratio of 0.5 %. The flow characteristics of the main vortex, generated at the nose of the main wing, and the smaller tip vortex are specified. The inboard motion of the main vortex with increasing angle of attack and the consequences for the load distribution are described. The free stream Mach number range of the test envelope is from 0.3 to 0.7. Therefore, transonic effects, especially shock–vortex interactions triggering vortex development, had to be analyzed for a safe design of the model. A peniche was designed to minimize the differences of the flow character compared to reference results of the model without wind tunnel walls. The effects of corner separation and displacement are specified at different stages of the iterative process. Finally, basic results for a pitching motion are discussed, based on global and distributed coefficients.

Item URL in elib:https://elib.dlr.de/90319/
Document Type:Article
Title:Vortical flow prediction for the design of a wind tunnel experiment with 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/s13272-014-0120-5
Page Range:pp. 1-13
Publisher:Springer
ISSN:1869-5582
Status:Published
Keywords:lambda wing, leading edge vortex, vortex–shock interaction, pitch oscillation
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 10:31
Last Modified:06 Sep 2019 15:24

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