Abstract: It is required the favorable controlled flight performance in full speed bound and wide flight airspace, wide range of mobility and horizontal landing capability for suborbital reusable launch vehicle (SRLV), which involve many field of aerodynamic problem: the subsonic, transionic, supersonic, hypersonic and rarefied field. Therefore the advanced aerodynamic configure design technology is one of the key technology for develop of SRLV. In this paper, engineering optimization method with Kriging response surface method is adopted to optimization flight aerodynamic characteristic with the engineering restriction for SRLV, the aerodynamic configure satisfied with the requirement is found. New method may be used to engineering design, and enhance the work efficiency.