Abstract
The spatially periodic system of dielectric barrier discharge actuators intended for laminar flow control on a swept wing is simulated numerically. Novel scheme of the actuator system ensuring the discharge formation only near one edge of every exposed electrode is proposed. The mathematical model of dielectric barrier discharge in air is formulated in the drift-diffusion approximation without convective transfer with taking into consideration the following volumetric reactions: the ionization of nitrogen and oxygen by electron impact, the electron attachment to oxygen, the electron detachment from negative ions of oxygen, the ion- ion recombination, the electron-ion recombination. Two types of boundary conditions on dielectric surface are considered for comparison: the model of instantaneous recombination and the model of finite rates of recombination and electron desorption. Numerical simulation of both conventional and novel schemes of plasma actuators is carried out for one set of problem parameters. Enhanced energy efficiency of the proposed scheme is demonstrated.
Highlights
The concept of laminar flow control (LFC) method on a swept wing based on an attenuation of the cross-flow-type instability due to electrogasdynamic (EGD) force impact on three-dimensional boundary layer in the vicinity of a wing leading edge was proposed at TsAGI some years ago [1]
Practical realization of the proposed method seems to become realistic owing to the usage of plasma actuators operating on the base of dielectric barrier discharge (DBD) [2]
Besides a miniaturization of DBD-actuators is necessary for practical realization of the mentioned LFC method because the boundary layer thickness in the vicinity of a swept wing leading edge of civil transonic airplane during cruise flight is very small
Summary
The concept of laminar flow control (LFC) method on a swept wing based on an attenuation of the cross-flow-type instability due to electrogasdynamic (EGD) force impact on three-dimensional boundary layer in the vicinity of a wing leading edge was proposed at TsAGI some years ago [1]. One can expect that a “filling” of the velocity profile in viscous flow along a critical line of a swept wing due to flow acceleration in this direction will result in some rise of the stability of this flow and, an increase in the critical Poll Reynolds number Practical realization of this LFC method demands development and optimization of multi-actuator system spatially periodic along a wing leading edge and ensuring EGD impact on large part of a wing surface. Main characteristics of various variants of the considered system of plasma actuators may be evaluated and compared on the base of numerical simulation with the use of proper mathematical models and computer codes
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
