A computer code for aeroelastic tailoring of a cranked-arrow wing for a supersonic transport is developed. The code includes static strength, local buckling, and aeroelastic analyses. The original finite element code is used for the static strength and local buckling analyses, and the original code is used for the vibration analysis of the aeroelastic analysis. In the optimization process of this code, a genetic algorithm is employed to find the optimum laminate construction of the wing box for which the structural weight is minimum under the static strength, local buckling, and aeroelastic constraints. These codes are applied to the preliminary design of a cranked-arrow wing. The optimum design satisfying only the static strength and local buckling constraints does not satisfy the aeroelastic constraint. Therefore, the flutter characteristics are optimized, and the optimum laminate construction that satisfies the static strength, local buckling, and aeroelastic constraints is obtained.