ABSTRACT

The quest to operate at the cutting edge of technology is a worthwhile effort but requires intensive research and brilliant implementation of logical thoughts aimed at an achievable objective. This gives distinct results with excellent achievements and impeccable brilliance in technology. This applies to optimization and multidisciplinary design optimization in engineering designs.

The objective is to achieve an optimum wing configuration defined by three design objectives within the aerodynamic and structural discipline – minimizing the maximum Von Mises stress; minimizing the maximum wing tip displacement; and maximizing the lift-drag coefficient – by varying the design sweep angle, dihedral angle, and the aspect ratio of the wing. This was achieved adopting a methodology that satisfies the NACA requirements for Multidisciplinary Design Optimization which highlights a framework that allows: automation; analyses and re-analyse; parameterization for easy modifications of design configurations; and leveraging existing tools and methods.

This was done using: CATIA for designing, parameterization and modelling; STAR CCM+ for computation of wing pressure loading; ANSYS for static structural analysis; and MATLAB as the central executive for the multi-objective optimization using a genetic algorithm. The result was not unique but was represented on a Pareto optimum on which any set of design parameter is optimum. This leaves the designer the flexibility on the Pareto optimum to trade off other objective(s) for objective(s) of higher importance.

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