3-section of cubic Bezier spline was used to fit the tangent of camber line and 2-section of cubic Bezier spline was used to fit the thickness distribution. The airfoil was built on streamline-surface. S1 flow field was evaluated by MISES software and optimization algorithm was performed by genetic algorithm(GA). By introducing a parallel mode to the traditional GA

computational efficiency was improved considerably. Automatic design and optimization of highly-loaded airfoil was achieved and the design criteria of highly-loaded airfoil for design of supersonic airfoil were investigated. Results show that compared with the original airfoil

incident angle range of airfoil I is broadened about 2 degree under the premise that loss coefficient of total pressure reduces a little and the airflow angle of outlet is unchanged; if loss coefficient of total pressure of airfoil II obviously reduces

incident angle range is broadened about 0.6 degree and deviation angle reduces about 3.9 degree.