Department of Aerospace Engineering,Sharif University of Technology
Department of Mechanical Engineering,Sharif University of Technology
Extensive tests were carried out on a section of a wind turbine blade. The eect 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 aects
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.