Abstract: The aerodynanic design criteria and design procedures for supercritical wing are established based on the computational aerodynamics. For supercritical airfoil design, the criteria contain (a) sonic plateau pressure distribution at off design condition, (b) retarding trailing edge flow separation, (c) near-zero angle of attack at design condition, and (d) local thickness constraints. For supercritical wing design, the criteria include (a) induced drag minimization under some constraints , (b) meeting stability requirement, (c) isobar pattern on the upper wing surface, and (d) cosidering elastic deformation of two wing. The supercritical wing design procedures can be divided into the phases, i.e. configuration design phase and aerodynamic efficiency optimization phase. The latter contains four steps: (a) basic airfoil design, (b) initial wing design, (c) cruise wing shape design, and (d) jig wing shape design. As a design example, a supercritical wing is designed and is tested in wind tunnel. The result indicates that the complete aircraft with the supercritical wing designed according to the present method has 12% higher cruise efficiency then a typical commercial airliner, although the former wing is 14% thicker than the latter one, which shows the present aerodynamic design method for supercritical wing is practically effective.

Key words: supercritical airfoil, supercritical wing, design, computational aerodynamics