翼型中平移边界层立体PIV测量检测方案(粒子图像测速)

This student research project deals with the investigations of the flow phenomena over a three dimensional moving airfoil. The complex motion apparatus was set up to create a pitching, plunging and rolling movement of a two dimensional wind tunnel model. The main objective was to determine the position of transition with respect to the phase angle and span-wise distribution. The campaign focussed Stereo PIV measurements, but also Mini Tuft-, Oilfilm- and SSLCC- Techniques, contributed to the results. It can be shown that the flow field is not dominated by side-wall effects, while the transition oscillates corresponding to the spanwise variation of the heaving cycle.