The design optimization of a wing for supersonic transport by means of Multiobjective Genetic Algorithm (MOGA) is presented. The objective function is to minimize the drag for transonic cruise, the drag for supersonic cruise and the bending moment at the wing root for the supersonic condition. The wing shape is defined by planform, thickness distributions and warp shapes, in total of 66 design ...

The current push for environmentally responsible aviation requires serious efforts to mitigate the escalating effects of such technology on climate change and natural resources. A clear vision for the efficiency of future transport aircraft – with specific targets for reduced fuel burn, emissions and noise – has been published in the U.S. National Aeronautics Research and Development Plan.1 As ...

In this paper, the exact discrete adjoint of an unstructured finite-volume formulation of the Euler equations in two dimensions is derived and implemented. The adjoint equations are solved with the same implicit scheme as used for the flow equations. The scheme is modified to efficiently account for multiple functionals simultaneously. An optimization framework, which couples an analytical shap...

In this paper we analyze inviscid aerodynamic shape optimization problems governed by the full potential and the Euler equations in two and three dimensions. The analysis indicates that minimization of pressure dependent cost functions results in Hessians whose eigenvalue distributions are identical for the full potential and the Euler equations. However, the optimization problems in two and th...

Decreasing the fuel consumption of road vehicles, due to environmental and selling arguments reasons, concerns car manufacturers. Consequently, improving the aerodynamism of car shapes, which implies reduction of drag coefficient, becomes one of the topic of automotive research centers. Hence, numerical shape optimization theory is applied to propose development process of a new car and innovat...

The research presented in this dissertation investigates the use of all-at-once methods applied to aerodynamic design. All-at-once schemes are usually based on the assumption of sufficient continuity in the constraints and objectives, and this assumption can be troublesome in the presence of shock discontinuities. Special treatment has to be considered for such problems and we study several app...