Localized micro-discharges group dielectric barrier discharge vortex generators: Disturbances source for active transition control. (January 2020)

• Record Type: Journal Article
• Authors: Moralev, Ivan; Bityurin, Valentin; Firsov, Alexander; Sherbakova, Victoria; Selivonin, Igor; Maxim, Ustinov
• Other Names: Knight Doyle D guest-editor.; Lipatov Igor guest-editor.
• Is Part Of: Proceedings of the Institution of Mechanical Engineers. Volume 234:Number 1(2020)
• Page Start: 42
• Page End: 57
• Publication Date: 2020-01
• Subjects: Boundary layer transition -- dielectric barrier discharge -- killer mode -- plasma actuators -- swept wing -- virtual roughness elements; Aeronautics -- Periodicals; Astronautics -- Periodicals; Airplanes -- Design and construction -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1177/0954410018796988
• Languages: English
• ISSNs: 0954-4100

Abstract

In this study, a new type of dielectric barrier discharge plasma actuator for boundary layer control, based on the controllable inhomogeneity of the discharge along the exposed electrode, is developed. The structure of the flow, generated by the isolated groups of microdischarges, was studied in detail in quiescent conditions. In the two-dimensional laminar boundary layer, the flow structure downstream of the actuator was studied for various sweep angles of the electrode. The equivalent model of the actuator, including the force and heat sources, is formulated based on the analysis of the flow created by the actuator in quiescent conditions. The model is verified by simulating the flow downstream of the actuator in two-dimensional boundary layer. As a final step, the applicability of the localized microdischarge group actuator for active transition control on a swept wing was studied. The generation of a cross-flow mode by the actuator was demonstrated in numerical simulation for low-velocity experiment conditions.