Advance ratio effects on the flow structure and unsteadiness of the dynamic-stall vortex of a rotating blade in steady forward flight
Abstract
The effect of advance ratio on the flow structures above a rotor blade in dynamic-stall is studied using stereoscopic particle image velocimetry. The dynamic-stall vortex shows a significant velocity component in its core, implying a helical structure progressing radially outboard. In addition, a dual-vortical structure was observed at inboard locations only at high advance ratios. The radial velocity attenuates at outboard locations, in contrast to the expected increase with centripetal acceleration. This attenuation is accompanied by an increase in unsteadiness of the vortex. The unsteadiness shows a low-frequency cycle-to-cycle variation despite steady freestream conditions and phase-locked blade tracking. Proper orthogonal decomposition analysis of the dominant flow mode confirms the unsteady behavior of the leading-edge vortex. The dependence on advance ratio is used to relate the unsteadiness of the dynamic-stall vortex to Coriolis effects.
Document Details
- Document Type
- Pub Defense Publication
- Publication Date
- Feb 01, 2015
- Source ID
- 10.1063/1.4906803
Entities
People
- Narayanan Komerath
- Vrishank Raghav
Organizations
- Army Research Office
- Georgia Tech