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Dynamic Stall Simulations on a Pitching Finite Wing

Kaufmann, Kurt and Merz, Christoph B. and Gardner, Anthony Donald (2016) Dynamic Stall Simulations on a Pitching Finite Wing. AIAA Aviation and Aeronautics Forum, 13. - 17. June 2016, Washington, D.C., USA.

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Official URL: http://www.aiaa-aviation.org/?_ga=1.190868137.266458715.1430135396

Abstract

The aerodynamic effects of dynamic stall on pitching wings and airfoils differ significantly from the static case, as soon as the static stall angle is exceeded. The large drag and pitching moment peaks associated with this phenomenon make it impossible to operate helicopters in flight conditions which trigger dynamic stall over large areas of the rotor blade. To simplify the problem, most of the research on dynamic stall focuses on two-dimensional pitching airfoils. This has lead to an understanding of the process and mechanism of dynamic stall, but has a limited insight into the three-dimensional nature of dynamic stall. There have been a few experimental and numerical studies on full helicopter configurations. These revealed the very complex flow field around the rotor blades, but the combination of downwash, blade-wakevortex interactions and the elasticity of the rotor blades leads to a limited comparability. An approach between these configurations is to use stiff pitching finite wings with defined boundary conditions. In these configurations the blade tip vortex reduces and delays the occurrence of dynamic stall in the surrounding region leading to a strongly three-dimensional flow, see e.g. Le Pape et al. and Lorber.

Item URL in elib:https://elib.dlr.de/99738/
Document Type:Conference or Workshop Item (Speech)
Additional Information:AIAA-2016
Title:Dynamic Stall Simulations on a Pitching Finite Wing
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Kaufmann, Kurtkurt.kaufmann (at) dlr.deUNSPECIFIED
Merz, Christoph B.christoph.merz (at) dlr.deUNSPECIFIED
Gardner, Anthony Donaldtony.gardner (at) dlr.deUNSPECIFIED
Date:2016
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Page Range:pp. 1-8
Series Name:Conference Proceedings
Status:Published
Keywords:dynamic stall,, DLR-TAU code, DAS-9A, helicopter, rotor blade
Event Title:AIAA Aviation and Aeronautics Forum
Event Location:Washington, D.C., USA
Event Type:international Conference
Event Dates:13. - 17. June 2016
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:rotorcraft
DLR - Research area:Aeronautics
DLR - Program:L RR - Rotorcraft Research
DLR - Research theme (Project):L - The Virtual Aerodynamic Rotorcraft
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Helicopters
Deposited By: Bachmann, Barbara
Deposited On:15 Mar 2017 11:48
Last Modified:15 Mar 2017 11:48

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