To enlarge application of the domestic supercomputers in aerospace industry, an approach of optimization design for the wing jigshape was developed to resolve practical problems from aerostructural design for high aspect ratio wing on these machines with the CFD software TRIP and the CSD software SiPESC, which have autonomous intellectual properties and abundant industrial applications. Highlight features about this approach are the modified threedimensional CST parameterization, parallelized evaluation for design sensitivities with the finite difference, and utilization of the largescale optimization algorithm such as the MMA. More important is the prediction of statically aeroelastic forces and loads, which is performed with the coupling software of TRIP and SiPESC. To exemplify its capability, aerodynamic shape and structural FEM of the CRM wing was modified as an initial jigshape through the elimination of twist and dihedral angle, and the augment of quadrilateral elements at wing LE and TE. The geometric twist distribution and the thickness of surface elements in the FEM were employed as design variables with the number of 10 000 around. Then the aeroelasticity optimization with 1g load and the structural optimization with 2.5g load were iterated to maximize the aerodynamic efficiency, and to minimize the structural weight. Primary results are the improvement of pitching moment coefficient of 40% without lessening of lift/drag ratio, and the weight reduction of 9% under the condition of maximum stress and displacement, which indicate that the approach and the software framework are feasible, even for more largescale problem due to the productlevel prediction capability of software and the divideandrule strategy in optimization process.