International Conference on Energy, Environment and Storage of Energy (ICEESEN)), Kayseri, Turkey, 19 - 21 November 2020, pp.114-118
This study provides details of an experimental investigation of a NACA2415 airfoil equipped with dielectric barrier discharge vortex generators at Reynolds number of 50000. The dielectric barrier discharge vortex generators are placed to the airfoil surface at x/C= 0.1. The lift and drag coefficients of the airfoil are obtained by using a six-axis load-cell system. The pressure distributions over the airfoils are measured using a pitot static tube system namely as a scanivalve unit and a pressure transducer. The experimental results showed that within the presented experimental conditions, the lift coefficient is increased and stall angle is postponed. DBD-VGs co-rotating plasma actuator structure is more effective than the counter-rotating model in reducing the drag coefficient. In addition, it appears that the effect is less in the case of the stall angle in both plasma actuated state, but they are more effective in the prestall angle and post-stall cases.