抄録
PARmetric SECtion (PARSEC ) airfoil can be used for efficient aerodynamic optimization and data mining, because each parameter is determined based on the aerodynamics regarding with the transonic wing. However it has problem that it is difficult to apply this method to a condition except transonic. A modified PARSEC method which solved that problem was suggested. In this study, this suggested method is applied to the design of SST multi-objective optimization is performed for airfoil representation in combination with Multi-Objective genetic algorithm (MOGA). The objective function was set as pressure drag and boom intensity minimization. The applicability of this method is verified from this result.
