Abstract
The coherent structure of a turbulent boundary layer in the vicinity of the trailing edge region of an airfoil is investigated experimentally. The airfoil (NACA 65-010) is located in a wind tunnel at an angle of attack of 0° and 8°. Conditional sampling with the VITA technique, and quadrant analysis are applied to make clear the coherent structure at the near wall region, which is called the bursting phenomenon. The main results obtained in this paper are summarized as follows : The contribution from the sweep event of the bursting phenomenon to the mean Reynolds stress -(uv)^^^→ increases at the suction side of an airfoil with an attack angle. However, at the pressure side, the contribution from the sweep event decreases, and that from the wallward interaction event increases. This is the reason that mean Reynolds stress increases at the suction side and decreases at the pressure side.
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