This study explores multiobjective aeroacoustic designs for flame deflector of a launch pad. The acoustic characteristics associated with deflector shapes are identified by multi- objective evolutionary computation with large eddy simulations. The objective functions in the multiobjective aeroacoustic design are designed to minimize (1) the spatial-averaged sound pressure level near the payload fairing, (2) the time-averaged maximum pressure on the curved surface of the frame deflector, and (3) the deviation of the curved surface from the at plate inclined at 45° The multiobjective evolutionary computation requires 2500 large eddy simulations. Evaluation of each single configuration required 130 nodes (1040 total cores) of a “K” supercomputer and 6 hour calculation. As the result of optimization, 146 nondominated solutions are obtained. The analysis of nondominated solutions clearly reveals various trade-off relations and correlations among the objective functions. The flow field analysis shows that as the curved surface around the impingement region becomes steeper, weaker acoustic waves are generated in the impingement region. This trend is related to the size of the separation bubble near the impingement region; as the surface steepens, the bubble shrinks. Furthermore, analysis of the effect of nozzle-to-launchpad distance on nondominated solutions are conducted to extract more useful knowledge for rocket launch site design.