This paper discusses a method to find an optimum design for a supersonic aircraft. The problem approached was optimizing the Lift-to-Drag ratio of an aircraft travelling at supersonic speeds. This was done through the use of Computer Aided Design (CAD) and Computational Fluid Dynamic (CFD) software. By setting up an initial model and allowing for several of the dimensions to be variable, a variety of aircraft shapes could be made to represent different design models. These models represented a population that could be optimized using a genetic algorithm. This paper utilized a Particle Swarm Optimization scheme, which led the population towards a converged solution. Stopping criteria was established to provide a stopping point for the population evolution and was met after four iterations.
Donahue, Daniel, "High Fidelity Conceptual Design of a Supersonic Aircraft" (2018). Optimization Methods in Engineering. 2.