Fuzzy Optimization of the Geometrical Parameters of Fighter Inlet

For two-dimensional, two-shock, all-external compression, supersonic, cheek-type inlet, the integrated aerodynamic-stealth design of geometrical parameters, such as width, ratio of width and height, angle of vertical compressing ramp, two cutting bevels of the lip plane and lip-position-angle, was investigated by considering those objectives such as the total pressure recovery coefficient, additional drag coefficient of supersonic overflow and the RCS(Radar Cross Section). The formulae for calculating the total pressure recovery coefficient, additional drag coefficient of supersonic overflow were derived. The satisfactory functions of the objectives and the restrictions were given, and then ,based on these functions, the multiobjective fuzzy optimization model was established.