Παραμετροποίηση αεροτομών δύο στοιχείων και ένταξη στην αεροδυναμική βελτιστοποίηση μορφής

In aerospace engineering design problems, aerodynamic shape optimization (ShpO) proves invaluable, as it enhances performance metrics and achieves potential targeted distributions.This diploma thesis develops a systematic process of optimizing the geometry of an airfoil in two distinct configurations, a normal and a deployed flap one.Computational fluid dynamics (CFD) methods are utilized for the solution of the governing (flow) equations.The two-element airfoil geometry is implemented in ShpO cases that aim to improve its main aerodynamic performance metrics, namely the drag at cruise and the lift at takeoff.With the purpose of addressing the challenges of aerodynamic ShpO, such as the computationally demanding CFD simulations, the nonlinear fluid physics and the mesh sensitivities, two different optimization methods are applied, specifically Metamodel Assisted Evolutionary Algorithms (MAEAs) and the adjoint method.An automatic process of generating the geometry of a two-element airfoil, in particular a main body and Fowler flap, is formulated.Using any airfoil's nodal coordinates as input, this process separates the airfoil into main body and flap, creates the flap's leading edge region and shapes the slot region of the main body so that it perfectly matches the flap.This is achieved by maintaining most of the airfoil nodes and designing Bézier curves, so that a realistic geometry with slope and curvature continuity is generated.The flap contour is then translated and rotated, as happens when ABC Adjoint Boundary Conditions AoA Angle of Attack CFD Computational Fluid Dynamics CP Control Point EA Evolutionary Algorithm EASY Evolutionary Algorithms SYstem FAE Field Adjoint Equations GUI Graphical User Interface LE Leading Edge LU Lower-Upper MAEA Metamodel Assisted EA MOO Multi-Objective Optimization