A combination of linear and nonlinear methods was found to be effective in designing a supersonic fighter wing. The design mach number was 1.6, with cruise and maneuver lift coefficients of 0.1 and 0.4. The planform was a tapered arrow wing with a subsonic leading edge. It was chosen based on general aerodynamic principles tempered with practical considerations. Initial camber and twist distributions were determined from a linear method. An Euler code was then used to improve upon the linear design; chordwise loading was made more uniform, and spanwise loading was adjusted toward the ideal elliptic distribution. The nonlinear calculations suggest the best approach is to use the linear method optimization at half the desired lift coefficient, and then to modify the design based on nonlinear analysis.