Aerodynamics Study of Fixed-Wing MAV: Wind Tunnel and Flight Test

Obtaining accurate aerodynamic characteristics of in-flight Micro Air Vehicles (MAVs) was viewed as difficult, due to the nature of very low Reynolds number, 3D complex flow, and strong influence from propulsion slipstream. This paper presents the study of the tailless, fixed-wing MAV, KuMAV-001, performed at Kasetsart University. The team investigated different analysis and testing methods to determine the aerodynamics characteristics of this MAV. The Vortex Lattice Method was introduced in the conceptual design phase and helped with the evaluation of the 3D effects for winglet configurations. The wind tunnel tests with main wing and fully configured MAV were conducted for powered and unpowered models. The influence of propulsion-induced flows on CL, CD, and CM(cg) was investigated during the wind tunnel testing. Verification of the performance results are to be completed with flight test data in the future