The Interactive Design Approach for Aerodynamic Shape Design Optimisation of the Aegis UAV

Azabi, Yousef; Chai, Runqi; Kipouros, Timoleon

doi:10.3390/aerospace6040042

Cited by 5 publications

(1 citation statement)

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“…In line with previous study, the multi-objective particle swarm optimization (MOPSO), employed in many multi-objective aerodynamic optimization, tried to get the Pareto-optimal front [35]. Azabi et al proposed an interactive MOPSO with the benefits of reducing computational time and avoiding the complexity of postdata analysis [36]. Huang et al constructed an improved MOPSO with principal component analysis methodology, enhancing the convergence of Pareto front [37].…”

Section: Introductionmentioning

confidence: 80%

Aerodynamic Design Optimization of Transonic Natural-Laminar-Flow Airfoil at Low Reynolds Number

Bian

2020

Mathematical Problems in Engineering

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The position and size of laminar separation bubble on airfoil surfaces exert a profound impact on the efficiency of transonic natural-laminar-flow airfoil at low Reynolds number. Based on the particle swarm algorithm, an optimization methodology in the current work would be established with the aim of designing a high and robust performance transonic natural-laminar-flow airfoil at low Reynolds number. This methodology primarily includes two design processes: a traditional deterministic optimization at on-design point and a multi-objective of uncertainty-based optimization. First, a multigroup cooperative particle swarm optimization was used to obtain the optimal deterministic solution. The crowing distance multi-objective particle swarm optimization and the non-intrusive polynomial chaos expansion method were then adopted to determinate the Pareto-optimal front of uncertainty-based optimization. Additionally, the γ−Re¯θt transition model was employed to predict the laminar-turbulent transition. Regarding to the established optimization methodology, a propeller tip airfoil of solar energy unmanned aerial vehicle was finally designed. During optimization processes, the minimized pressure drag was particularly chosen as the optimization objective, while the friction drag increment served as a constraint condition. The deterministic results indicate that the optimized airfoil has a good ability to control the separation and reattachment positions, and the pressure drag can be greatly reduced when the laminar separation bubble is weakened. The multi-objective results show that the uncertainty-based optimized airfoil possesses a significant robust performance by considering the uncertainty of Mach number. The findings evidently demonstrate that the proposed optimization methodology and mathematical model are valuable tools to design a high-efficiency airfoil for the propeller tip.

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Section: Introductionmentioning

confidence: 80%