抄録
The present study investigates a periodic wake passing induced boundary layer transition on a flat-plate subjected to favorable and adverse pressure gradients. The aim is to exploit unsteady effects in order to design a turbine blade without increasing the profile loss, as has been achieved for low pressure turbine blade. Detailed boundary layer measurements were conducted using a hot-wire probe. A passage-contouring device was employed to generate on the test model a pressure gradient which is typical to that generated by a turbine blade. A wake generating squirrel cage was used to create periodic wakes in front of the flat plate. It was found that the effect of turbulent spots due to the wake passing was confirmed distributions of raw velocity signals measured at y=0.2mm under the influence of a passage contouring device.
