Simulation investigation into the aerodynamic traits of an asymmetric folding-wing unmanned aerial vehicle

A model of an asymmetric Folding-Wing UAV was established, and numerical simulations were conducted to study its aerodynamic characteristics. Aerodynamic data, such as lift coefficient, drag coefficient, lift-to-drag ratio, and rolling moment coefficient, were extracted at different angles of attack. Flow field pressure contour maps were compared. At the same time, the evolution law analysis of the dynamic pressure profile in the flow field and the spatial distribution characteristics of the pressure gradient were obtained. The reasons for the rolling moment generated by the folding wing aerodynamic layout were evaluated. Based on the above research, the consequence shows that: the maximum lift coefficient of the folding wing UAV occurs at an AOA of 9°, and the minimum drag coefficient occurs at an AOA of -4°; As the Mach number increases from 0.09 to 0.13, the lift coefficient correspondingly increases by 2% to 6%, and the drag coefficient significantly increases by 9% to 38%. The asymmetric folded wing layout results in an asymmetric pressure profile on the upper superficies of the body, which decreases first and then increases with the increase of the AOA.