Plasma Thermal Efect Excitation Flow Control Analysis

At present,the aerodynamic characteristics of wings and flow control of airfoil surfaces is one of the important research directions of modern flying machines,and its research continues to receive the attention of many scholars and aerospace companies in various countries.Improvements in drag and lift reduction can significantly reduce the cost of flight and optimise the aerodynamic performance of the aircraft.In order to investigate the aerodynamic performance of the airfoil,the optimal airfoil NACA0012 was selected through hydrodynamic simulation studies for symmetric airfoils with different relative thicknesses,and the optimal airfoil NACA0012 was compared and analysed based on Fluent simulation software using the SST k-ω turbulence model,and the simulation results were compared with experimental data to verify the feasibility of the model.The effects of airfoil type NACA0012 on its maximum lift coefficient and maximum lift-to-drag ratio are investigated at different Mach numbers,Reynolds numbers and head angles.Characterise the stall condition of the wing through numerical analysis.The flow control technique of plasma thermal excitation is analysed by numerical simulation.In this paper,the flow control of lift and drag reduction of the airfoil is carried out by coupling the simplified UDF source term file of the arc discharge plasma excitation on the airfoil surface with the Fluent solver based on the "image-only" simulation modelling method.In this paper,the plasma excitation is applied to the airfoil.In this paper,the plasma excitation is applied to the upper and lower surfaces and the leading and trailing edges of the airfoil in order to find the optimum location for increasing lift and reducing drag.At the same time,the physical mechanisms of single and double excitation are explained to some extent.The effect of plasma excitation on the effect of plasma excitation at different Reynolds number,angle of approach and excitation intensity is investigated through hydrodynamic simulations.The effect of plasma excitation on the airfoil excitation in solving the airfoil stall problem is analysed and studied.In order to effectively control the size of the plasma excitation area and to facilitate the change of the excitation location,numerical expressions for the airfoil are used to determine the excitation location,the excitation area size and the magnitude of the energy input,which are calculated using UDF source term files in conjunction with the Fluent solver.The results show that the airfoil exhibits an increase in lift and reduction in drag under plasma action,but the excitation effect is strongly influenced by the position.The effect of plasma excitation on the suppression of flow separation in the flow separation region of the upper airfoil surface is analysed and investigated,as the effect of plasma excitation varies over a specific range of Reynolds number,head angle and excitation intensity.On the one hand,this paper complements the database of flow field characteristics of low velocity symmetric airfoils,and on the other hand,it presents the law of flow control effect on airfoils under the effect of plasma thermal excitation.