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Unsteady aerodynamic effects in small-amplitude pitch oscillations of an airfoil
KTH, School of Engineering Sciences (SCI), Mechanics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW. KTH, Centres, SeRC - Swedish e-Science Research Centre.
KTH, School of Engineering Sciences (SCI), Mechanics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW. KTH, Centres, SeRC - Swedish e-Science Research Centre.ORCID iD: 0000-0001-6570-5499
KTH, School of Engineering Sciences (SCI), Mechanics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW. KTH, Centres, SeRC - Swedish e-Science Research Centre.ORCID iD: 0000-0002-5913-5431
KTH, School of Engineering Sciences (SCI), Mechanics. KTH, School of Engineering Sciences (SCI), Centres, Linné Flow Center, FLOW. KTH, Centres, SeRC - Swedish e-Science Research Centre.ORCID iD: 0000-0001-9627-5903
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2018 (English)In: International Journal of Heat and Fluid Flow, ISSN 0142-727X, E-ISSN 1879-2278, Vol. 71, p. 378-391Article in journal (Refereed) Published
Abstract [en]

High-fidelity wall-resolved large-eddy simulations (LES) are utilized to investigate the flow-physics of small-amplitude pitch oscillations of an airfoil at Rec=100,000. The investigation of the unsteady phenomenon is done in the context of natural laminar flow airfoils, which can display sensitive dependence of the aerodynamic forces on the angle of attack in certain “off-design” conditions. The dynamic range of the pitch oscillations is chosen to be in this sensitive region. Large variations of the transition point on the suction-side of the airfoil are observed throughout the pitch cycle resulting in a dynamically rich flow response. Changes in the stability characteristics of a leading-edge laminar separation bubble has a dominating influence on the boundary layer dynamics and causes an abrupt change in the transition location over the airfoil. The LES procedure is based on a relaxation-term which models the dissipation of the smallest unresolved scales. The validation of the procedure is provided for channel flows and for a stationary wing at Rec=400,000.

Place, publisher, year, edition, pages
Elsevier, 2018. Vol. 71, p. 378-391
Keywords [en]
Dynamic-response, Laminar separation bubble, Local stability, Transition, Unsteady aerodynamics, Wall-resolved les
National Category
Fluid Mechanics and Acoustics Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-228734DOI: 10.1016/j.ijheatfluidflow.2018.04.009Scopus ID: 2-s2.0-85046802460OAI: oai:DiVA.org:kth-228734DiVA, id: diva2:1210670
Funder
VINNOVA, 2014-00933EU, European Research Council, 694452-TRANSEP-ERC-2015-AdGSwedish e‐Science Research Center
Note

QC 20180529

Available from: 2018-05-29 Created: 2018-05-29 Last updated: 2018-07-02Bibliographically approved

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Vinuesa, RicardoHanifi, ArdeshirSchlatter, PhilippHenningson, Dan S.

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Negi, Prabal SinghVinuesa, RicardoHanifi, ArdeshirSchlatter, PhilippHenningson, Dan S.
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MechanicsLinné Flow Center, FLOWSeRC - Swedish e-Science Research Centre
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International Journal of Heat and Fluid Flow
Fluid Mechanics and AcousticsVehicle Engineering

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