1
Department of Aerospace Engineering,Sharif University of Technology
2
Department of Mechanical Engineering,Sharif University of Technology
Abstract
Extensive tests were carried out on a section of a wind turbine blade. The e ect of reduced
frequency on the boundary layer transition point of the model oscillating in plunge has been investigated.
The spatial-temporal progressions of the transition point and the state of the unsteady boundary layer were
measured using multiple hot- lm sensors. The measurements showed that reduced frequency highly a ects
variations of the transition point and results in a hysteresis loop in the dynamic transition locations. The
dominated frequencies of the boundary layer are found to be a function of the reduced frequency and mean
angle of attack.
