elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Impressum | Datenschutz | Kontakt | English
Schriftgröße: [-] Text [+]

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

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.

Dieses Archiv kann nicht den Volltext zur Verfügung stellen.

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/
Dokumentart:Zeitschriftenbeitrag
Titel:Effect of the Model-Sidewall Connection for a Dynamic Stall Airfoil Experiment
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Gardner, Anthony D.anthony.gardner (at) dlr.dehttps://orcid.org/0000-0002-1176-3447NICHT SPEZIFIZIERT
Richter, KaiKai.Richter (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
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:
HerausgeberInstitution und/oder E-Mail-Adresse der HerausgeberHerausgeber-ORCID-iDORCID Put Code
NICHT SPEZIFIZIERTAIAANICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
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

Nur für Mitarbeiter des Archivs: Kontrollseite des Eintrags

Blättern
Suchen
Hilfe & Kontakt
Informationen
electronic library verwendet EPrints 3.3.12
Gestaltung Webseite und Datenbank: Copyright © Deutsches Zentrum für Luft- und Raumfahrt (DLR). Alle Rechte vorbehalten.