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The development and application of a rapid methodology for the optimization of HighLift configurations is here presented. The proposed framework includes a quasi-threedimensional method to simulate the aerodynamic performance, a rapid method for the estimation of the static aero-elastic effects, and two multi-objective optimization algorithms: the well-know NSGA-II and the innovative multi-objective Tabu Search. After an extensive validation study of both the aerodynamic simulation and the aero-structure coupling method, the framework is used to optimize the landing performance of the KH3Y configuration. The deployment settings of the full-span slat and of the two single-slotted flap elements, inboard and outboard, are identified as design variables. The maximum lift coefficient and the lift over drag ratio at the approach angle of attack are used as objective functions. Two optimization setups are executed to assess the influence of the wing flexibility on the revealed Pareto Front. In both cases the selected optimization algorithm has been able to improve the performance of the datum. Moreover, the results show the importance of considering aero-structure influences early on in the design process. Finally, parallel coordinate visualization techniques are used to analyze the peculiar Search Pattern revealed. NomenclatureK Stiffness matrix S Flexibility matrix u Displacements array Z Forces and moments array cd Drag coefficient cl Lift coefficient cl appr Lift coefficient at approach angle of attack L/D appr Lift to Drag ratio at approach angle of attack M Number of wing sections spanwise * EngD Researcher, School of Engineering, Centre for Propulsion. Student Member. g.trapani@cranfield.ac.uk

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