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Unsteady Boundary Layer Transition on the DSA-9A Rotor Blade Airfoil

Autor(en): K. Richter, S. Koch, A. Goerttler, B. Lütke, C.C. Wolf, A. Benkel
Zusammenfassung: The unsteady boundary layer transition on the pitching helicopter main rotor blade airfoil DSA-9A was experimentally investigated by the use of hot film anemometry and unsteady pressure measurements. The unsteady flow characteristics on the upper and the lower side of the airfoil were analyzed for steady test cases and dynamic cases with sinusoidal pitching motion in attached flow conditions at M = 0:30 and Re = 1:8106. The paper discusses the unsteady transition characteristics in detail and presents the influence of the pitching frequency on the unsteady transition. The results indicate that a large transition hysteresis exists on both sides of the airfoil, and that the hysteresis is much larger than can be explained by the unsteadiness in lift. Significant transition zones exist on the airfoil with sizes of up to 55% chord. The frequency influence is seen in an increase in the hysteresis and in a reduction of the size of the transition zone with increasing frequency.
Veranstaltung: 41th European Rotorcraft Forum 2015
Medientyp: Conference Paper
Sprache: englisch
Veröffentlicht: DGLR-Bericht, 2016, 2016-01, 41st European Rotorcraft Forum 2015; S.-; 2016; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn
Preis: NA
Stichworte zum Inhalt: pressure measurement;airfoils;boundary layer transition;flow characteristics;frequencies;hysteresis;pitching moments;rotary wings;sine waves;unsteady flow;velocity measurement
Verfügbarkeit: Bestellbar
Veröffentlicht: 2016

Dieses Dokument ist Teil einer übergeordneten Publikation:
41st European Rotorcraft Forum 2015