Abstract
The wing shape of booster stage for Two-Stage-To-Orbit Reusable Launch Vehicle is optimized in consideration of supersonic region, transonic cruise and subsonic landing. Navier-Stokes computation is used for aerodynamic evaluation because transonic cruise and subsonic landing have flow condition that vorticity dominants. ARMOGA is used for aerodynamic optimization problem with four objective functions because it is expected that tradeoff can be obtained using low individual numbers. The results show the relationship of each objective functions.
