Efficient prediction of aerodynamic characteristics of flexible flapping wings based on unsteady panel method

The assessment of aerodynamic performance is crucial for designing Flapping-Wing Micro Air Vehicles (FWMAVs), yet limited research has addressed the prediction and analysis of flexible wing aerodynamics during the preliminary design phase. This study proposes an efficient prediction method for the aerodynamic characteristics of flexible flapping wings. A conical surface model is introduced to mimic wing deformation, and the unsteady panel method is employed to predict aerodynamic characteristics. The wing deformation characteristics, the influence of membrane tightness on aerodynamics and the control moments as well as additional moments resulting from coupled control based on the two-winged FWMAV configuration have been investigated. Results indicate that the current prediction method effectively captures the deformation and aerodynamic characteristics of flexible flapping wing. A relatively slack membrane enhances aerodynamic efficiency when the lift is satisfactory. The roll, pitch, and yaw moments correlate linearly with the root vein deflection angle in baseline case, while excessive membrane tension reduces or reverses control effectiveness. The additional roll moment resulting from coupled pitch and yaw controls is significantly greater than the other two additional moments. The findings provide valuable insights for the aerodynamic and control design of flexible flapping wings.