Effect Of Taper Ratio On Lift And Drag Force On Swept RAE2822 Wing

In this study,the RAE 2822 wing profile,which is suitable for transonic flights,was performed by using six different angle of attack in different taper ratios(0.075,0.16,0.25,0.35,0.45,0.6,0.8)and sweep angles(20°,25°,30°,35°,40°).As a result of these combinations of geometries analyses,the effect of taper ratio on lift and drag forces have been investigated from different perspectives,and it has been revealed with its advantages and disadvantages.Firstly,the models were constructed in Solid Works 2017 and then imported to the Pointwise V17.3R1 program to set mesh structure and boundary conditions.After that FLUENT 16,which is popular CFD software,was used to analysis all models for Reynolds number is 5.54x10~6,and Mach number is 0.8 at 10000 meters altitude.As solver and turbulent model,density-based and standard k-?were chosen.The results obtained from the FLUENT software are shown with graphs and contours,and the results are compared and discussed with each other.It was observed that the best performance ratio was realized at the 2-degree angle of attack from the graph of C_L/C_D coefficient which was formed to evaluate the performance of the lift and drag forces of the aircraft wing.And considering 2 degree angle of attack,the highest value of C_L/C_D is found as 30.3398 where taper ratio of 0.075 and sweep angle of 40°at 2 degree attack angle and the lowest value of C_L/C_D is found as 7.0589 where taper ratio of0.075 and sweep angle of 20°at 9 degree attack angle.In addition,the highest lift force is produced as 40.84108 Ton where taper ratio of 0.8 and sweep angle of 20°at the 2-degree attack angle,and the lowest drag force is produced as 0.73168225 Ton where taper ratio of0.0.075 and sweep angle of 40°at the 2-degree attack angle.In the light of these results,it is shown that wings with low taper ratio are more efficient than wings with large taper ratio.However,there are some disadvantages with small taper ratio wings,although they have better values in terms of C_L/C_D values.One of these is that the risk of tip stall is high in the wings with a small taper ratio.This is understood from the graphics of distribution of the lift force along the spanwise.Another disadvantage is the turbulence intensity of the wings with a small taper ratio when the pressure,velocity,streamline,and wake turbulence contours are formed at the wing tip.