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Dynamic Effects in the Reverse Flow Velocity Field

[+] Author Affiliations
Dhwanil Shukla, Nandeesh Hiremath, Vrishank Raghav, Narayanan Komerath

Georgia Tech, Atlanta, GA

Paper No. AJKFluids2015-13545, pp. V001T13A002; 8 pages
doi:10.1115/AJKFluids2015-13545
From:
  • ASME/JSME/KSME 2015 Joint Fluids Engineering Conference
  • Volume 1: Symposia
  • Seoul, South Korea, July 26–31, 2015
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 978-0-7918-5721-2
  • Copyright © 2015 by ASME

abstract

At high edgewise flow speeds, reversed flow causes excursions in pitching moment and blade torsion on the rotor blades of helicopters and wind turbines. Our prior work has shown that a yawed fixed wing at angle of attack in reversed flow generates a sharp-edge vortex. The sharp-edge vortex is a primary feature of the flow under the rotor blade. During operation as a rotor blade at high advance ratio in a wind tunnel, stereo PIV results show that the well-formed sharp-edge vortex at 240 degrees azimuth resembles that on a forward-swept wing. This vortex stops growing before 270 degrees and convects with the blade by 300 degrees. Static pressure computed from interpolated velocity data show the effects of vortex-induced radial pressure gradient. This explains the finding of inboard-directed radial flow at 300 degrees azimuth, overcoming centrifugal effects. Viscous stress is shown to have only a minor effect on the static pressure field computation.

Copyright © 2015 by ASME
Topics: Flow (Dynamics)

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