In this research, multiobjective optimization system has been developed to reduce the aerodynamic drag and the sonic boom for SST wing-body configuration. Wing and fuselage are defined by 131 design variables and optimized at the same time. Multiblock grids around SST wing-body configuration are generated automatically and an Euler solver is used to evaluate the aerodynamic performance of SST wing-body configuration. Sonic boom is evaluated based on the equivalent area distribution by Darden. MOGA is used as an optimizer of the present optimization. To reduce the large computation time, CFD computations are parallelized by a simple master-slave concept on SGI ORIGIN 2000 at The Institute of Fluid Science at Tohoku University.
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