抄録
In low Reynolds number region about order of 1,000 to 10,000, aerodynamic characteristics of NACA0012 airfoil shows unique characteristics because of appearance of laminar separation and separation bubble on the airfoil. Lift characteristics, especially, strongly show non-linear characteristics with decreasing of its Reynolds number, and performance of the airfoil becomes worse because of involving the separated flow on the airfoil. We applied a DBD plasma actuator on the airfoil that it aims to control and suppress the separation of boundary layer on the airfoil, and performed measurements of aerodynamic forces and flow field of the airfoil. As the results of measurements, it is clearly confirmed that the aerodynamic characteristics were improved by using the plasma actuator. Moreover, improvement effect on the aerodynamic characteristics show different one due to changing of installed position of the plasma actuator on the airfoil.
