On the possibility of laminar flow control on a swept wing by means of plasma actuators

Theoretical assessment of the possibility of laminar flow control (LFC) on a swept wing owing to volumetric force and heat impact of plasma actuators is presented. The proposed approach includes numerical modeling of dielectric barrier discharge (DBD) actuators, calculation of inviscid flow over an infinite span swept wing, calculation of compressible boundary layer spatially modulated in spanwise direction, and numerical solution of linear stability problem for stationary modes of cross-flow-type disturbances. Calculations have been performed for one set of geometrical and physical parameters describing plasma actuators to estimate qualitative features of volumetric force and heat input distributions. Inviscid flow and boundary layer calculations were executed at free stream parameters corresponding to typical cruise flight conditions. Estimation of volumetric force impact necessary for noticeable influence on cross-flowtype instability is obtained

ON THE POSSIBILITY OF LAMINAR FLOW CONTROL ON A SWEPT WING BY MEANS OF PLASMA ACTUATORS

Theoretical assessment of the possibility of laminar §ow control (LFC) on a swept wing owing to volumetric force and heat impact of plasma actua-tors is presented. The proposed approach includes numerical modeling of dielectric barrier discharge (DBD) actuators, calculation of inviscid §ow over an in¦nite span swept wing, calculation of compressible boundary layer spatially modulated in spanwise direction, and numerical solution of linear stability problem for stationary modes of cross-§ow-type dis-turbances. Calculations have been performed for one set of geometrical and physical parameters describing plasma actuators to estimate quali-tative features of volumetric force and heat input distributions. Inviscid §ow and boundary layer calculations were executed at free stream pa-rameters corresponding to typical cruise §ight conditions. Estimation of volumetric force impact necessary for noticeable in§uence on cross-§ow-type instability is obtained.