Aerospace, Vol. 10, Pages 907: Turbulent Boundary Layer Separation Control Using Magnetohydrodynamic Plasma Actuator

Aerospace, Vol. 10, Pages 907: Turbulent Boundary Layer Separation Control Using Magnetohydrodynamic Plasma Actuator

Aerospace doi: 10.3390/aerospace10110907

Authors: Alexander Kotvitskii Pavel Kazanskii Ivan Moralev

The pulse electric arc discharge in an external magnetic field is studied as a vortex generator in the subsonic boundary layer. A pulsed Ampere force induces a hairpin vortex near the wall; its structure depends on the relative direction of arc propagation and external flow velocity. The data presented in this article were obtained from parametric studies of vortex characteristics and their effects on the boundary layer profile at various actuator momentum coefficients (Cμ=1−30) and vortex sizes relative to the boundary layer thickness (D/δ=0.5−1.2). Also, the control of turbulent boundary layer separation on a bump at a flow velocity up to 50 m/s was attempted. An average shift of the separation line by 15% of the bump height was obtained at a flow velocity of 50 m/s and a total momentum coefficient of 0.6%.