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Effect of the Model-Sidewall Connection for a Dynamic Stall Airfoil Experiment

Gardner, Anthony D. and Richter, Kai (2020) Effect of the Model-Sidewall Connection for a Dynamic Stall Airfoil Experiment. Journal of Aircraft, 57 (1), pp. 1-6. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.C035613. ISSN 0021-8669.

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Official URL: https://doi.org/10.2514/1.C035613


The performance assessment of helicopter rotor blade airfoils no longer relies only on wind-tunnel testing for performance data in the linear region. For many flow cases, the computational fluid dynamics (CFD) is currently mature enough to give a reliable prediction of the airfoil performance. However, around maximum lift (and for dynamic stall performance), CFD can be more expensive and less reliable. In the past [1], the effect of the sidewall interaction was noted to vary widely between wind tunnels. As noted in Ref. [2], the sidewall connection geometry of the interface between the airfoil and the wind-tunnel wall can have a significant effect on the local corner flow. However at the airfoil midline, the difference between a gap and a solid connection was not detectable for a static flow at moderate airfoil lift. For Ref. [2], the sidewall effect required an additional angle-of-attack correction, as seen in the literature [3-5], which caused a decrease in the gradient of the lift polar for this type of solid-wall wind tunnel [6-8], but the total effect was relatively minor. Similarly, Ref. [9] showed that the difference between twodimensional (2-D) computations and the wind-tunnel data could be almost fully accounted for by considering the gap between the airfoil and the wind-tunnel wall. However, other authors [10,11] have noted that, particularly for dynamic stall test cases, wall interferences are propagated into the airfoil midline, causing significant differences in the dynamic stall lift and pitching-moment peaks, which characterize the flow. Ericson and Reding [12] noted that the main effect of the wind tunnel is to reduce the height of dynamic stall peaks, but more modern efforts [10] note that it is difficult to separate a sidewall correction from a generation of strongly three-dimensional (3-D) flow, which breaks the 2-D assumption of airfoil testing.

Item URL in elib:https://elib.dlr.de/131992/
Document Type:Article
Title:Effect of the Model-Sidewall Connection for a Dynamic Stall Airfoil Experiment
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Gardner, Anthony D.UNSPECIFIEDhttps://orcid.org/0000-0002-1176-3447UNSPECIFIED
Date:January 2020
Journal or Publication Title:Journal of Aircraft
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
Page Range:pp. 1-6
EditorsEmailEditor's ORCID iDORCID Put Code
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
Series Name:Engineering Notes
Keywords:dynamic stall, rotor blades
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 (old)
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Helicopter, GO
Institute for Aerodynamics and Flow Technology > High Speed Configurations, GO
Deposited By: Carter, Beatrice
Deposited On:11 Dec 2019 11:55
Last Modified:24 Oct 2023 14:40

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