Optimization Design of the Wing of Cruise Missile on the Basis of the Vortex Lattice Approach

Abstract Aerodynamic performance of missile wings is a vital factor affecting the endurance and combat effectiveness of cruise missiles. Given the current situation that the aerodynamic design of conventional cruise missile wings is less and there is more room for improvement, a missile wing shape with a winglet is considered designed to improve the cruise characteristics of cruise missiles effectively. Firstly, the EPPLER 66 is selected as the wing shape by the combination of vortex surface element approach batch calculation and CFD simulation analysis. According to the dimensional parameters of a typical patrol wing, the design variables and corresponding optimization intervals are determined, and the aerodynamic optimization is carried out by combining the genetic approach as well as the vortex lattice approach. CFD is used to verify the aerodynamic performance of the optimized wing. The calculation outcomes reveal that the optimized wing has a ratio of lift-to-drag of 23.43, which is 12.32% higher than that of the conventional flat wing.