TY - GEN
T1 - Characterization of a three-dimensional leading-edge separation bubble on swept, low aspect-ratio propeller blades
AU - Maldonado, Ye Bonne Koyama
AU - Delattre, Gregory
AU - Illoul, Cedric
AU - Dejeu, Clement
AU - Jacquin, Laurent
N1 - Publisher Copyright:
Copyright © 2017 ASME.
PY - 2017/1/1
Y1 - 2017/1/1
N2 - Leading-edge vortex flows are often present on propeller blades at take-off, however, their characteristics and aerodynamic impact are still not fully understood. An experimental investigation using Time Resolved Particle Image Velocimetry (TR-PIV) has been performed on a model blade in order to classify this flow with respect to both delta wing leading-edge vortices and the low Reynolds number studies regarding leadingedge vortices on rotating blades. A numerical calculation of the experimental setup has been performed in order to assess usual numerical methods for propeller performance prediction against TR-PIV results. Similar characteristics were found with non slender delta wing vortices at low incidence, which hints that the leading-edge vortex flow may generate vortex lift. The influence of rotation on the characteristics of the leading-edge vortex is compared to that of the pressure gradient caused by the circulation distribution. A discussion on the quality of the PIV reconstruction for close-wall structures is provided.
AB - Leading-edge vortex flows are often present on propeller blades at take-off, however, their characteristics and aerodynamic impact are still not fully understood. An experimental investigation using Time Resolved Particle Image Velocimetry (TR-PIV) has been performed on a model blade in order to classify this flow with respect to both delta wing leading-edge vortices and the low Reynolds number studies regarding leadingedge vortices on rotating blades. A numerical calculation of the experimental setup has been performed in order to assess usual numerical methods for propeller performance prediction against TR-PIV results. Similar characteristics were found with non slender delta wing vortices at low incidence, which hints that the leading-edge vortex flow may generate vortex lift. The influence of rotation on the characteristics of the leading-edge vortex is compared to that of the pressure gradient caused by the circulation distribution. A discussion on the quality of the PIV reconstruction for close-wall structures is provided.
UR - https://www.scopus.com/pages/publications/85028993784
U2 - 10.1115/GT2017-64545
DO - 10.1115/GT2017-64545
M3 - Conference contribution
AN - SCOPUS:85028993784
T3 - Proceedings of the ASME Turbo Expo
BT - Aircraft Engine; Fans and Blowers; Marine; Honors and Awards
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
Y2 - 26 June 2017 through 30 June 2017
ER -