Optimization and Design of a Flexible Droop Nose Leading Edge Morphing Wing Based on a Novel Black Widow Optimization (B.W.O.) Algorithm—Part II

This work presents an aerodynamic and structural optimization for a Droop Nose Leading Edge Morphing airfoil as high lift device the UAS-S45. The results were obtained using three algorithms: coupled Particle Swarm Optimization-Pattern Search, Genetic Algorithm, Black Widow Optimization algorithm. lift-to-drag ratio was used fitness function, impact of choice algorithm selection on function evaluated. carried out at various Mach numbers 0.08, 0.1, 0.15, respectively, cruise take-off flight conditions. All these algorithms effectively comparable with differences less than 0.03% similar geometries pressure distributions. In addition, unsteady analysis Variable dynamic meshing scheme to study its flow behaviour different angles attack feasibility leading-edge downward deflection stall control mechanism. numerical showed that variable morphing leading edge reduces separation areas over increases angle attack. Furthermore, preliminary investigation conducted into design sensitivity structure UAS-S45 wing integrated internal actuation correlation determination matrices computed composite geometry obtain parameters highest coefficients. include material qualities, thickness, ply angles, stacking sequence. These findings can be utilized flexible skin framework, target droop nose deflections edge, improved model.