Aerodynamic Evaluation of UiTM's Blended Wing Body Unmanned Aerial Vehicle at Different Elevon Configurations using Vortex Lattice Method

This paper presents findings of the preliminary aerodynamic evaluation for UiTM's baseline model blended wing body (BWB) unmanned aerial vehicle (UAV). The UAV design is based on a new planform and hence its characteristics were yet to be understood. The design is tailless, with both the inboard and outboard control surfaces act as elevons as its main control surface elements. Vortex lattice method (VLM) simulation analysis was conducted to investigate how different elevon configurations affected the aircraft's attitude. The elevons were categorized as inboard -only (IE), outboard -only (OE), and combined inboard and outboard (PSE) configurations. For the analysis, the configurations were varied in three different deflection angles: 5 degrees up, 0 degrees neutral and 5 degrees down. The obtained analysis results showed that the highest maximum lift -to -drag ratio, L/D max achieved was 16.748. The results also confirmed that the UAV would be required to operate at a slight pitch -up attitude angle of attack of 5 degrees for steady level flight, at which the lift coefficient, C L was found to be 0.307. Additionally, the results highlighted "pure roll" characteristic, as well as confirmed the presence of "adverse yaw," in certain elevon configurations.