26 翼まわりの流れでのスポイラーの影響

抄録

Unsteady flow fields around an airfoil with a spoiler of different sizes at various positions on its surface were visualized experimentally using aluminum dust and electrolysis precipitation methods. Also, they are visualized numerically by using a discrete vortex method. The agreement between the experimental and computational results were found to be very good. The forces acting on the airfoil show strong unsteadiness when a small spoiler is located near the leading edge, while it changes periodically when it is near the trailing edge. This corresponds well to the visualized vortex shedding.