剥離泡を伴う翼面境界層に及ぼす静止円柱後流通過の効果(流体工学,流体機械)

抄録

This paper describes an attempt to clarify effects of stationary bar wakes upon blade boundary layer with separation bubble. This study aims at exploration of a possibility for reducing the aerodynamic loss due to the boundary layer around blades in turbomachines. The test model used in this study consists of semi-circular leading edge and two parallel flat plates. Detailed flow measurements over the test model are conducted using a single hot-wire probe. Emphasis in this study in placed on the effect of bar shifting or bar clocking across the inlet flow in order to see how the bar-wake position against the test model affects the separation bubble as well as aerodynamic loss generated within the boundary layer. The present study reveals a loss reduction through the separation bubble control using a properly clocked bar wake.