Flow Structures and Aerodynamic Behavior of a Small-Scale Joined-Wing Aerial Vehicle under Subsonic Conditions

Flow behavior and aerodynamic performance of a small-scale joined-wing unmanned aerial vehicle (UAV) was studied experimentally numerically under various pitch yaw angle combinations in subsonic flow conditions. Selected numerical results are compared against experimental obtained using surface oil visualizations force measurements, with additional simulations expanding the range combined configurations. Under zero-yaw conditions, increasing leads to formation symmetric ogive vortex roll-ups close fuselage their significant interactions fore-wing. Additionally, contributions lift drag coefficients conditions by key UAV components have been documented detail. In contrast, when is subjected yaw, no clear evidence such can be observed. Instead, asymmetric separations occur over fuselage’s port side resemble bluff-body behavior. these become more complex, they interact fore- aft-wings increases. Lift variations due different also documented. Finally, rolling yawing moment suggest that present possesses adequate flight stability unless angles high.