Advance ratio effects on the flow structure and unsteadiness of the dynamic-stall vortex of a rotating blade in steady forward flight
Author:
Affiliation:
1. School of Aerospace Engineering, Georgia Institute of Technology, 270 Ferst Drive, Atlanta, Georgia 30332, USA
Funder
Army Research Office
Publisher
AIP Publishing
Subject
Condensed Matter Physics,Fluid Flow and Transfer Processes,Mechanics of Materials,Computational Mechanics,Mechanical Engineering
Link
http://aip.scitation.org/doi/pdf/10.1063/1.4906803
Reference33 articles.
1. The effect of advance ratio on the aerodynamics of revolving wings
2. Rotational accelerations stabilize leading edge vortices on revolving fly wings
3. Dynamic stall on a fully equipped helicopter model
4. A comprehensive PIV measurement campaign on a fully equipped helicopter model
5. Velocity measurements on a retreating blade in dynamic stall
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