Abstract: Structured chimera grid method has been considered as the most applicable technology to solve aerodynamic problems of multi-component configuration aircraft at current stage. Therefore, by using structured chimera technology and CFD method, two typical aerodynamic problems of conventional tactics missile configuration with rudder deflection were thoroughly investigated: i) a simple and practical linear modification model for micro unsymmetry configuration was proposed which could effectively reduce the range of error and eliminate its skewness properties caused by asymmetric separation vortex, while the traditional method introduced lateral aerodynamic error in data transformation; ii) 3-tunnel linear adding model was investigated and the research shows that linear model’s error was mainly caused by the sharing rudder’s nonlinear performance, and the coupling losses of the steerage has also been quantitatively evaluated.

Key words: CFD, chimera grid, aircraft, multi-body aerodynamics