Abstract
A Multi-Objective Genetic Algorithm (MOGA) is applied in search of the optimal fuel injector shape in the supersonic combustor. The optimal shape is investigated in terms of rapid mixing of fuel jet and supersonic airstream. Two goals, those are to maximize the jet core height and to minimize the total pressure loss, are adopted for the optimization. The numbers of injector holes are restricted during the evolution process. Consequently, pareto fronts under the 2 and 3 holes quantity constraints evolve successfully.
