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Dynamic Stall Simulations on a Pitching Finite Wing

Kaufmann, Kurt and Merz, Christoph B. and Gardner, Anthony Donald (2017) Dynamic Stall Simulations on a Pitching Finite Wing. Journal of Aircraft. American Institute of Aeronautics and Astronautics (AIAA). DOI: 10.2514/1.C034020 ISSN 0021-8669

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Unsteady Reynolds-averaged Navier-Stokes computations were carried out on a pitching finite wing model using the finite volume solver DLR-TAU. The comparison with the experimental data reveals a good agreement, especially in the region of the first occurrence of stall. Discrepancies are observed in the blade tip region, where the flow in the numerical data shows a stronger separation along with larger hysteresis effects in contrast to the experiment. An investigation with different pitching frequencies revealed a change in the sequence of dynamic stall vortex formation in the spanwise direction. For the lowest frequency the propagation of the stall vortex starts at the wing tip and then spreads rootwards, whereas for the higher frequencies the first evolution of the dynamic stall vortex starts further inboard, subsequently propagating in tipward and rootward directions. An investigation using a γ-Reθt approach demonstrated that small differences can be attributed to transition, nevertheless these can give further insight in the physics of dynamic stall and improve the comparability with the experiment. A comparison with two-dimensional simulations shows strong similarities in the sections where the vortex starts to evolve and large differences in the surrounding areas.

Item URL in elib:https://elib.dlr.de/104312/
Document Type:Article
Additional Information:Vol. 54, No. 4, July-August 2017
Title:Dynamic Stall Simulations on a Pitching Finite Wing
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
Journal or Publication Title:Journal of Aircraft
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
DOI :10.2514/1.C034020
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Keywords:dynamic stall, DLR-TAU code, DAS-9A, helicopter, rotor blade, transition
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 for Aerodynamics and Flow Technology > Helicopter, GO
Deposited By: Bachmann, Barbara
Deposited On:18 Jan 2017 16:32
Last Modified:08 Mar 2018 18:41

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