Numerical Study On Lift Enhancement And Drag Reduction Of NACA0012 Airfoil Based On Plasma Thermal Effect

The research on the aerodynamic characteristics of the aircraft plays a very important part in modern fluid mechanics and how to improve the aerodynamic performance of the aircraft is the focus of researchers.The aerodynamic characteristics of NACA0012 low speed symmetrical airfoil are studied.At the same time,the effects of increasing lift and reducing drag under the influence of plasma are studied.The research is based on the CFD software and uses the SST k-? low-speed turbulence model.It is studied that the effects of the Mach number and Reynolds number on the NACA0012 airfoil's maximum lift coefficient,slope of lift curve and maximum lift-drag ratio.The stalling problem of NACA0012 airfoil at subsonic speed is also studied and the stall angle of attack of the airfoil is quantitatively described by fitting curve expression.Based on the thermal effect,the effects of single and double excitation on the Lift enhancement and drag reduction of NACA0012 airfoil are studied.By applying plasma excitation to the upper and lower surfaces of the airfoil and the front and rear edges,the best position for increasing lift and reducing drag is found.At the same time,the physical mechanism of single excitation and double excitation is explained.In order to speed up the calculation of the model in the CFD software,the solution steering is used to solve the airfoil in Fluent and reasonable boundary conditions are set to ensure the accuracy of the solution results.The irrelevance of the calculation model grid is verified.The calculation results are compared with Ladson's experimental data and it is concluded that the model is feasible.A method is proposed to define the excitation position by using the expression of two-dimensional airfoil.It can not only ensure that the excitation area is close to the surface of the airfoil,but also quickly change the excitation position.The method of program automatic solution is used to calculate the lift and drag coefficient of airfoil.The application of the plasma area and the position change are also achieved by programming.The results show that the aerodynamic characteristics of airfoil are correlated with Mach number and Reynolds number.The airfoil shows the effect of increasing lift and reducing drag under the effects of plasma,but the excitation effect is greatly affected by the position.On the one hand,the flow field characteristic database of low-speed symmetrical airfoil is supplemented.On the other hand,the law of increasing lift and reducing drag of airfoil under the effects of plasma thermal effect is put forward.