Repozytorium publikacji - Politechnika Gdańska

This paper presents a part of the works conducted in the Plasmaero European project (task 3.1), where the trailing-edge flow separation of a NACA 0015 airfoil has been controlled using four different dielectric barrier discharge (DBD) actuator types at three institutions across Europe. The results show that it is possible to enhance the aerodynamic performance of aircraft at speeds up to 40 m/s. Dielectric-barrier-discharge vortex generators (DBD VGs) have been used to create streamwise vortices that entrain the high-speed fluid from outside the boundary layer into the separated region causing flow reattachment. The DBD VGs have shown the ability of flow separation control by reducing the drag of the NACA 0015 airfoil up to 45%. Single dielectric barrier discharge (SDBD) and multi dielectric barrier discharge (MDBD) plasma actuators have been used to re-energize the separated region by introducing high streamwise velocity close to the wall. The novel MDBD actuators create an induced velocity above 10 m/s. This significant improvement in actuator authority has yielded flow separation control at a Reynolds number of Rec = 1.33×106, where a drag reduction of 10% was observed.

Autorzy

• R. D. Whalley,
• A. Debien,
• J. Podliński,
• T. N. Jukes,
• K.-S. Choi,
• N. Benard,
• E. Moreau,
• Artur Berendt link otwiera się w nowej karcie ,
• J. Mizeraczyk