Numerical analysis of the aerodynamic performance on wings with morphed trailing edges for MAV applications

Wing morphing can improve aircraft performance at various periods of flight. Furthermore, exploration was restricted due to restrictions in aerodynamic performance parameters of the morphed wing from such a flexible trailing edge. The continuous morphing of the variable trailing edge has been simulated using the computational fluid dynamic approach and java foil tools. Current research has focused on stable aerodynamic features of morphing wings with morphing trailing edges. The influence of (AoA)-the angle of attack and deflection angle of aerodynamic forces and moments has been studied. A technique for delaying stalling was developed using the morphing trailing edge wing's aerodynamic features. The computational results indicate that the coefficient of lift in the deflecting process is less significant at a low AoA-angle attack than in the static scenario. Increasing the deflection rate then increases the lift coefficient and decreases the drag coefficient. However, the lift coefficients are more significant for greater angles of attack than in the static position and drag, and when it rises as the deflection increases, the rate. Furthermore, the systematic deviation of the morphing trailing edge with a slight deflection angle and a high deflecting rate can increase the lift, drag, and lift-to-drag ratio.