An optimal aerodynamic design for the wing of a wide-body long-range aircraft

Results of the optimal aerodynamic design of a wide-body long-range aircraft wing at high transonic flight speeds are presented. The problem is solved using the approach based on methods of high-precision mathematical modeling and global optimum search with application of supercomputer technologies. It is shown that the optimal wing is characterized by a low shockwave drag at the main design point and can operate under given cruise flight conditions. Optimization technology made it possible to shift the Mach tuck towards larger Mach numbers. The aerodynamic characteristics of the optimal wing significantly outperform those of the original wing in a wide range of the Mach number and lift coefficient. The optimal wing satisfies all the given geometric and aerodynamic constraints.