低Re数領域でのNACA0012翼まわりの流れ場

第1報 翼後流の特性

抄録

Measurements of velocity distributions immediately behind the trailing edge of NACA0012 airfoil at low Reynolds numbers were carried out to disclose the relation between the aerodynamic characteristics described in the previous report and the flow fields around the airfoil. A dead-air region due to laminar separation, which spoils the linear growth of lift, is created near the trailing edge of the airfoil at low angles of attack. A laminar separation bubble is observed in the boundary layer on the upper surface at intermediate angles of attack and the existence of the bubble might be responsible for the constant slope of the lift curve. Blunt decrease in lift peculiar to the stall of airfoils at low Reynolds numbers is characterized by the gradual expansion of turbulent separated region.