Gardner, Anthony D. und Richter, Kai (2020) Effect of the Model-Sidewall Connection for a Dynamic Stall Airfoil Experiment. Journal of Aircraft, 57 (1), Seiten 1-6. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.C035613. ISSN 0021-8669.
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Offizielle URL: https://doi.org/10.2514/1.C035613
Kurzfassung
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.
elib-URL des Eintrags: | https://elib.dlr.de/131992/ | ||||||||||||
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Dokumentart: | Zeitschriftenbeitrag | ||||||||||||
Titel: | Effect of the Model-Sidewall Connection for a Dynamic Stall Airfoil Experiment | ||||||||||||
Autoren: |
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Datum: | Januar 2020 | ||||||||||||
Erschienen in: | Journal of Aircraft | ||||||||||||
Referierte Publikation: | Ja | ||||||||||||
Open Access: | Nein | ||||||||||||
Gold Open Access: | Nein | ||||||||||||
In SCOPUS: | Ja | ||||||||||||
In ISI Web of Science: | Ja | ||||||||||||
Band: | 57 | ||||||||||||
DOI: | 10.2514/1.C035613 | ||||||||||||
Seitenbereich: | Seiten 1-6 | ||||||||||||
Herausgeber: |
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Verlag: | American Institute of Aeronautics and Astronautics (AIAA) | ||||||||||||
Name der Reihe: | Engineering Notes | ||||||||||||
ISSN: | 0021-8669 | ||||||||||||
Status: | veröffentlicht | ||||||||||||
Stichwörter: | dynamic stall, rotor blades | ||||||||||||
HGF - Forschungsbereich: | Luftfahrt, Raumfahrt und Verkehr | ||||||||||||
HGF - Programm: | Luftfahrt | ||||||||||||
HGF - Programmthema: | Hubschrauber | ||||||||||||
DLR - Schwerpunkt: | Luftfahrt | ||||||||||||
DLR - Forschungsgebiet: | L RR - Rotorcraft Research | ||||||||||||
DLR - Teilgebiet (Projekt, Vorhaben): | L - Der virtuelle Drehflügler (alt) | ||||||||||||
Standort: | Göttingen | ||||||||||||
Institute & Einrichtungen: | Institut für Aerodynamik und Strömungstechnik > Hubschrauber, GO Institut für Aerodynamik und Strömungstechnik > Hochgeschwindigkeitskonfigurationen, GO | ||||||||||||
Hinterlegt von: | Carter, Beatrice | ||||||||||||
Hinterlegt am: | 11 Dez 2019 11:55 | ||||||||||||
Letzte Änderung: | 24 Okt 2023 14:40 |
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