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
Abstract
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/ | |||||||||
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Document Type: | Article | |||||||||
Title: | Effect of the Model-Sidewall Connection for a Dynamic Stall Airfoil Experiment | |||||||||
Authors: |
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Date: | January 2020 | |||||||||
Journal or Publication Title: | Journal of Aircraft | |||||||||
Refereed publication: | Yes | |||||||||
Open Access: | No | |||||||||
Gold Open Access: | No | |||||||||
In SCOPUS: | Yes | |||||||||
In ISI Web of Science: | Yes | |||||||||
Volume: | 57 | |||||||||
DOI : | 10.2514/1.C035613 | |||||||||
Page Range: | pp. 1-6 | |||||||||
Editors: |
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Publisher: | American Institute of Aeronautics and Astronautics (AIAA) | |||||||||
Series Name: | Engineering Notes | |||||||||
ISSN: | 0021-8669 | |||||||||
Status: | Published | |||||||||
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: | 03 Sep 2020 12:56 |
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