Quasi-3D Aerodynamic Analysis Method for Blended-Wing-Body UAV Configurations

The current study presents a low-fidelity, quasi-3D aerodynamic analysis method for Blended-Wing-Body (BWB) Unmanned Aerial Vehicle (UAV) configurations. A tactical BWB UAV experimental prototype is used as reference platform. utilizes 2D panel analyses and theoretical calculations to rapidly compute lift pitching moment coefficients. philosophy the underlying semi-empirical equations of proposed are extensively described. Corrections related control surfaces deflection ground effect also suggested, so that stability trimming can be supported. validated against low-fidelity 3D methods high-fidelity, Computational Fluid Dynamics (CFD) results various validation procedures show considerably more accurate than existing ones, provide predictions both coefficients requires far less computational resources time when compared CFD modeling. Hence, it serve valuable aerodynamics tool