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Unsteady pressure distributions at the wind tunnel model of a pitching Lambda wing with development of vortical flow

Wiggen, Stefan (2015) Unsteady pressure distributions at the wind tunnel model of a pitching Lambda wing with development of vortical flow. Aerospace Science and Technology, 47, 396 - 405. Elsevier. doi: 10.1016/j.ast.2015.10.007. ISSN 1270-9638.

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Offizielle URL: http://www.sciencedirect.com/science/article/pii/S1270963815003168

Kurzfassung

Abstract Unsteady pressure distributions at a pitching Lambda wing with 53° sweep angle are described in this paper. The tests with a half wing model with a purely round leading edge were conducted in the Transonic Wind Tunnel Göttingen. The free stream Mach number was varied between 0.3 and 0.7. Oscillation frequencies up to 22 Hz and amplitudes smaller than 1° were used. The pressure distributions suggest flow conditions that can be divided into three Regimes, depending on the mean angle of attack: I) Above 10°, at the rear outboard part of the wing, the suction increases which is caused by a vortical flow occurring close to the surface. A strong suction peak emerges at the leading edge. II) At higher angles of attack, the strong suction peak at the leading edge breaks down, and a typical hump like pressure distribution below a vortex core is generated further downstream. This is the sign for a vortex flow further separating from the surface. Features of a vortex breakdown can be found. However, it lacks the typical signs for a transformation from a jet-like to a wake-like flow. III) Finally, the low pressure region below the vortex moves inboard and a deadwater type of flow exists at the outboard part of the wing. The unsteady pressure distributions strongly depend on the mean angle of attack. The highest unsteady pressures occur in Regimes II and III. Especially the out of phase parts drastically increase in Regime II. Furthermore, the quasi-steady effects strongly lag the motion. This means, the sign of the imaginary part of the unsteady pressure distribution is opposite to that of the real part. The lag increases with frequency. For angles of attack above that of the maximum lift, the negative lift slope turns positive with increasing frequency due to the strong lag of the vortex.

elib-URL des Eintrags:https://elib.dlr.de/101594/
Dokumentart:Zeitschriftenbeitrag
Titel:Unsteady pressure distributions at the wind tunnel model of a pitching Lambda wing with development of vortical flow
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Wiggen, StefanStefan.Wiggen (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:Dezember 2015
Erschienen in:Aerospace Science and Technology
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Ja
In ISI Web of Science:Ja
Band:47
DOI:10.1016/j.ast.2015.10.007
Seitenbereich:396 - 405
Verlag:Elsevier
ISSN:1270-9638
Status:veröffentlicht
Stichwörter:Unsteady pressure, Lambda wing, pitching
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Luftfahrt
HGF - Programmthema:Flugzeuge
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L AR - Aircraft Research
DLR - Teilgebiet (Projekt, Vorhaben):L - Flugphysik (alt)
Standort: Göttingen
Institute & Einrichtungen:Institut für Aeroelastik > Aeroelastische Experimente
Hinterlegt von: Wiggen, Stefan
Hinterlegt am:13 Jan 2016 11:32
Letzte Änderung:31 Okt 2023 11:16

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