Two-Way Coupled Aero-structural Optimization of Stable Flying Wings

An aero-structural algorithm to optimize a flying wing in cruise conditions for preliminary design is developed using two-way interaction between the structure and aerodynamics. A particle swarm routine employed solve multi-objective optimization, aiming reduce weight of aerodynamic drag at point. Different shapes are evaluated during optimization process until reaches optimal aspect ratio, taper angle incidence, twist angle, swept airfoil shape, where six-parameters method allow reflex airfoils. main isotropic I-beam models structure. extended vortex lattice model aerodynamics, along with high-order panel fully coupled viscous interaction. The finite element used flying-wing under static loads. iterate deflection its impact on aerodynamics convergence reached. constraints implemented into objective function fulfil structural criteria longitudinal stability. comparison against baseline carried out, achieving higher efficiency promising results elliptical lift distribution, high margin, without use non-constant twist. suggest that combining both airfoils sweep washout solution weight, keeping stability tailless aircraft lower end transonic regime.